阅读说明：本技术 风扇容纳壳体 (Fan housing ) 是由 凯文·米 戴维·格罗夫斯 于 2019-07-12 设计创作，主要内容包括：一种用于在燃气涡轮发动机中容纳风扇叶片的结构支撑壳体包括至少一个区域,在该至少一个区域中,两个或更多个纤维增强复合材料的子层压件由延展性聚合材料彼此间隔开。(A structural support case for housing fan blades in a gas turbine engine includes at least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material.)

1. A hardwall fan containment case (22) for containing fan blades in a gas turbine engine (10), the hardwall fan containment case (22) comprising at least one region (30) in which two or more fiber reinforced composite (31, 32, 33) sub-laminates are spaced apart from one another by a ductile polymeric material (34, 35).

2. A hardwall fan containment case (22) according to claim 1, wherein the ductile polymeric material (34, 35) has a tensile modulus of no more than about 50% of the tensile modulus of the fibre-reinforced composite material (31, 32, 33), such as no more than about 25% of the tensile modulus of the fibre-reinforced composite material.

3. A hard-walled fan containment case (22) according to claim 1 or claim 2 wherein the ductile polymeric material (34, 35) has a tensile modulus of no greater than about 10GPa, such as no greater than about 5 GPa.

4. A stiff-walled fan containment case (22) according to any preceding claim, wherein the ductile polymeric material (34, 35) has an elongation to failure of at least five times, such as at least ten times, the elongation to failure of the fibre-reinforced composite material (31, 32, 33).

5. A hard-walled fan containment case (22) according to any preceding claim wherein the ductile polymeric material (34, 35) has an elongation to failure of at least about 50%, such as at least about 100%.

6. A stiff-walled fan containment case (22) according to claim 5, wherein the fiber-reinforced composite material (31, 32, 33) has an elongation to failure of no more than about 10%, or such as no more than about 5%.

7. A hardwall fan containment case (22) according to any preceding claim, wherein the fibre reinforced composite (31, 32, 33) has a tensile strength of at least about 1000Mpa and the ductile polymeric material (34, 35) has a tensile strength of no more than about 200 Mpa.

8. A hard-walled fan containment case (22) according to any preceding claim wherein the ductile polymeric material (34, 35) is not susceptible to thermal degradation at temperatures of 200 ℃ or below.

9. A hard-walled fan containment case (22) according to any preceding claim wherein the malleable polymeric material (34, 35) comprises polyurethane and/or phenolic resin and the fibre-reinforced composite material (31, 32, 33) is a fibre-reinforced polymer, such as a carbon fibre-reinforced polymer.

10. A hard-walled fan containment case (22) according to any preceding claim wherein the two or more sub-laminates of fibre-reinforced composite material (31, 32, 33) are spaced apart from one another by one or more solid layers of non-reinforced ductile polymeric material (34, 35).

11. A hard-walled fan containment case (22) according to any preceding claim wherein the thickness of the ductile polymeric material (34, 35) disposed between each pair of adjacent sub-laminates of the fibre-reinforced composite material (31, 32, 33) is no greater than the thickness of any of the pair of two or more sub-laminates of the fibre-reinforced composite material, for example wherein the thickness of the ductile polymeric material disposed between each pair of adjacent sub-laminates of the fibre-reinforced composite material is no greater than about 50% of the thickness of any of the two or more sub-laminates of the fibre-reinforced composite material.

12. A hard-walled fan containment case (22) according to any preceding claim wherein two or more sub-laminates of fibre-reinforced composite material (31, 32, 33) extend around a majority of the circumference of the structural support case (22) in which the at least one region (30) is spaced from one another by a ductile polymeric material (34, 35).

13. A gas turbine engine (10) comprising a hardwall fan containment case (22) according to any preceding claim.

14. A method of laying down a preform for a hardwall fan containment case (22) for containing fan blades in a gas turbine engine (10), the method comprising: applying a first fiber reinforced composite sub-laminate to a tool (101); applying a ductile polymeric material to the first fiber reinforced composite sub-laminate (102); and applying a second fiber reinforced composite sub-laminate to the ductile polymeric material (103).

15. A method of manufacturing a hardwall fan containment case (22) for containing fan blades in a gas turbine engine (10), the method comprising laying down a preform for the hardwall fan containment case by the method of claim 14 and curing the preform (104).

Technical Field

The present disclosure relates to structural support housings for housing fan blades in gas turbine engines.

Background

The gas turbine engine includes a fan having fan blades located forward of the engine. The fan may be accommodated in a hard-walled fan accommodating case (case). During operation, any of the fan blades may break away from the fan and impact the hard-walled fan containment case. This is commonly referred to as a Fan Blade Out (FBO) event. After a turbine engine fan loses blades, the load on the fan containment case is much higher than it would be under normal flight conditions due to fan imbalance. During engine shutdown (typically on the order of a few seconds), cracks may propagate rapidly in the hard-walled fan containment case due to damage caused by the impact of the FBO, which may lead to containment failure.

Hardwall fan containment cases are typically made of titanium and are designed to resist broken blades. Recently, hard-walled fan containment cases made of fiber reinforced composite materials have been proposed. Composite fan containment cases are strong and typically lighter than titanium cases, but may be susceptible to brittle fracture under the impact of broken fan blades.

Disclosure of Invention

According to a first aspect, there is provided a structural support case for housing fan blades in a gas turbine engine, the structural support case comprising at least one region in which two or more sub-laminates of fibre-reinforced composite material are spaced apart from each other by a ductile polymeric material.

The structural support housing may be a fan containment housing (e.g., a fan containment case). The structural support housing may be a hard-walled fan containment housing (e.g., a hard-walled fan containment housing). The structural support housing may be a barrel of a hard-walled fan containment housing.

The ductile polymeric material may be more ductile (i.e., less brittle) than the fiber-reinforced composite material.

The ductile polymeric material may have an elongation to failure greater than the elongation to failure of the fiber-reinforced composite. The ductile polymeric material may have an elongation to failure of at least about five times, such as at least about ten times, or at least about fifteen times, or at least about twenty times, or at least about thirty times, or at least about forty times the elongation to failure of the fiber-reinforced composite. The fiber reinforced composite may have an elongation to failure of no greater than about 20% of the elongation to failure of the ductile polymeric material, such as no greater than about 10% of the elongation to failure of the ductile polymeric material, or no greater than about 5% of the elongation to failure of the ductile polymeric material, or no greater than about 1% of the elongation to failure of the ductile polymeric material.

The ductile polymeric material may have an elongation to failure of at least about 50%, such as at least about 75%, or at least about 100%, or at least about 125%, or at least about 150%, or at least about 175%, or at least about 200%. The fiber reinforced composite may have an elongation to failure of about 100% to about 500%. The ductile polymeric material may have an elongation to failure of about 450%. The fiber reinforced composite may have an elongation to failure of no greater than about 5%, such as no greater than about 4%, or no greater than about 3%.

It will be understood that the term "elongation to failure" (alternatively referred to as "ultimate elongation" or "tensile strain") is a standard measure of the ductility of a material, i.e., the amount of strain that a material can withstand before failing during a tensile test. The elongation to failure of a material is determined as the strain at which a sample of the material subjected to a tensile load fails and is measured in percent strain units, for example, according to ASTM D882.

The ductile polymeric material may be less stiff (i.e., more flexible) than the fiber-reinforced composite material.

The tensile modulus of the ductile polymeric material may be lower than the tensile modulus of the fiber-reinforced composite material. The tensile modulus of the ductile polymeric material may be no greater than about 50% of the tensile modulus of the fiber reinforced composite, such as no greater than about 40% of the tensile modulus of the fiber reinforced composite, or no greater than about 30% of the tensile modulus of the fiber reinforced composite, or no greater than about 25% of the tensile modulus of the fiber reinforced composite, or no greater than about 20% of the tensile modulus of the fiber reinforced composite, or no greater than about 15% of the tensile modulus of the fiber reinforced composite, or no greater than about 10% of the tensile modulus of the fiber reinforced composite. The tensile modulus of the fiber-reinforced composite may be at least about two times, such as at least about three times, or at least about four times, or at least about five times, or at least about six times, or at least about seven times, or at least about eight times, or at least about nine times, or at least about ten times, the tensile modulus of the ductile polymeric material.

The tensile modulus of the ductile polymeric material may be not greater than about 15GPa, such as not greater than about 10GPa, or not greater than about 5GPa, or not greater than about 3GPa, or not greater than about 2GPa, or not greater than about 1 GPa. The tensile modulus of the ductile polymeric material may be about 0.01GPa to about 2 GPa. The tensile modulus of the ductile polymeric material may be about 0.1 GPa. The tensile modulus of the fiber-reinforced composite material may be not less than about 70GPa, such as not less than about 80GPa, or not less than about 90GPa, or not less than about 100GPa, or not less than about 110GPa, or not less than about 120 GPa.

It is to be understood that the term "tensile modulus" refers to the modulus of elasticity when measured in tension, i.e., young's modulus. The tensile modulus of a material is determined as the ratio of stress to strain along the axis of a sample of the material to which a tensile force is applied, measured at a relatively low strain that makes hooke's law applicable (i.e., in the linear region of the stress-strain plot), for example, according to ASTM D882.

The ductile polymeric material may have a shear modulus that is lower than the shear modulus of the fiber-reinforced composite material. The ductile polymeric material may have a shear modulus of no greater than about 50% of the shear modulus of the fiber-reinforced composite, such as no greater than about 40% of the shear modulus of the fiber-reinforced composite, or no greater than about 30% of the shear modulus of the fiber-reinforced composite, or no greater than about 25% of the shear modulus of the fiber-reinforced composite, or no greater than about 20% of the shear modulus of the fiber-reinforced composite, or no greater than about 15% of the shear modulus of the fiber-reinforced composite, or no greater than about 10% of the shear modulus of the fiber-reinforced composite. The shear modulus of the fiber-reinforced composite material may be at least about two times, such as at least about three times, or at least about four times, or at least about five times, or at least about six times, or at least about seven times, or at least about eight times, or at least about nine times, or at least about ten times, the shear modulus of the ductile polymeric material.

The shear modulus of the ductile polymeric material may be not greater than about 15GPa, such as not greater than about 10GPa, or not greater than about 5GPa, or not greater than about 3GPa, or not greater than about 2GPa, or not greater than about 1 GPa. The ductile polymeric material may have a shear modulus of about 0.01GPa to about 2 GPa. The ductile polymeric material may have a shear modulus of about 0.1 GPa.

It is to be understood that the term "shear modulus" (also referred to as "modulus of rigidity") refers to the modulus of elasticity when measured under shear. The shear modulus of a material is determined as the ratio of shear stress to shear strain in a sample of the material to which shear force is applied, measured in the linear elastic region of the shear stress-strain plot at relatively low shear strain, for example, according to ASTM D882.

The fiber-reinforced composite may be stronger than the ductile polymeric material. For example, the tensile strength of the ductile polymeric material may be lower than the tensile strength of the fiber-reinforced composite material. Additionally or alternatively, the yield strength of the ductile polymeric material may be lower than the yield strength of the fiber-reinforced composite material.

The tensile strength of the ductile polymeric material may be no greater than about 50% of the tensile strength of the fiber reinforced composite, such as no greater than about 40% of the tensile strength of the fiber reinforced composite, or no greater than about 30% of the tensile strength of the fiber reinforced composite, or no greater than about 20% of the tensile strength of the fiber reinforced composite, or no greater than about 10% of the tensile strength of the fiber reinforced composite, or no greater than about 5% of the tensile strength of the fiber reinforced composite. The tensile strength of the fiber-reinforced composite may be no less than about two times the tensile strength of the ductile polymeric material, such as no less than about five times the tensile strength of the ductile polymeric material, or no less than about ten times the tensile strength of the ductile polymeric material.

The tensile strength of the ductile polymeric material may be not greater than about 200Mpa, such as not greater than about 150Mpa, or not greater than about 100Mpa, or not greater than about 50 Mpa. However, the tensile strength of the ductile polymeric material may be not less than about 1MPa, such as not less than about 5MPa, or not less than about 10 MPa. The tensile strength of the ductile polymeric material may be about 15Mpa to about 150 Mpa. The tensile strength of the ductile polymeric material may be about 30 MPa. The tensile strength of the fiber reinforced composite may be not less than about 500Mpa, such as not less than about 750Mpa, or not less than about 1000Mpa, or not less than about 1250Mpa, or not less than about 1500 Mpa.

It is to be understood that the term "tensile strength of a material" refers to the Ultimate Tensile Strength (UTS) of the material, i.e., the maximum stress to which a sample of the material is subjected when the sample is tensile loaded until failure, e.g., according to ASTM D882.

The yield strength of the ductile polymeric material may be no greater than about 50% of the yield strength of the fiber reinforced composite, such as no greater than about 40% of the yield strength of the fiber reinforced composite, or no greater than about 30% of the yield strength of the fiber reinforced composite, or no greater than about 20% of the yield strength of the fiber reinforced composite, or no greater than about 10% of the yield strength of the fiber reinforced composite, or no greater than about 5% of the yield strength of the fiber reinforced composite. The yield strength of the fiber-reinforced composite may be no less than about two times the yield strength of the ductile polymeric material, such as no less than about five times the yield strength of the ductile polymeric material, or no less than about ten times the yield strength of the ductile polymeric material.

The yield strength of the ductile polymeric material may be no greater than about 100Mpa, such as no greater than about 75Mpa, or no greater than about 50 Mpa. However, the ductile polymeric material may have a yield strength of at least about 0.5MPa, such as at least about 1 MPa. The yield strength of the fiber-reinforced composite material may be not less than about 500Mpa, for example, or not less than about 750Mpa, or not less than about 1000 Mpa.

It is to be understood that the term "yield strength" (also referred to as "yield stress") refers to the stress at which a material begins to plastically deform in a tensile test, i.e., the deformation is inelastic and therefore non-recoverable at and above that stress. Yield strength can be identified, for example, by stress according to ASTM D882, at which the relationship between stress and strain (on the stress-strain graph) becomes non-linear.

Brittle materials may fail without or with little plastic deformation when tested under tensile loads, such that the yield strength of the material is substantially equal to the ultimate tensile strength of the material. The fiber-reinforced composite may be more brittle than ductile. Accordingly, the yield strength of the fiber-reinforced composite material may be the same as the tensile strength of the fiber-reinforced composite material. The ductile polymeric material may have a yield strength of no greater than about 50% of the tensile strength of the fiber reinforced composite, such as no greater than about 40% of the tensile strength of the fiber reinforced composite, or no greater than about 30% of the tensile strength of the fiber reinforced composite, or no greater than about 20% of the tensile strength of the fiber reinforced composite, or no greater than about 10% of the tensile strength of the fiber reinforced composite, or no greater than about 5% of the tensile strength of the fiber reinforced composite. The tensile strength of the fiber-reinforced composite may be no less than about two times the yield strength of the ductile polymeric material, such as no less than about five times the yield strength of the ductile polymeric material, or no less than about ten times the yield strength of the ductile polymeric material.

The fiber-reinforced composite may be more ductile than the ductile polymeric material.

The ductile polymeric material may have a fracture toughness that is lower than the fracture toughness of the fiber-reinforced composite. The fracture toughness of the fiber-reinforced composite material may be at least about two times, such as at least about five times, the fracture toughness of the ductile polymeric material. The ductile polymeric material may have a fracture toughness of no greater than about 50% of the fracture toughness of the fiber-reinforced composite, such as no greater than about 25% of the fracture toughness of the fiber-reinforced composite. The ductile polymeric material may have a fracture toughness of no greater than about 10MPa m^1/2E.g., not greater than about 5MPa m^1/2. The ductile polymeric material may have a fracture toughness of not less than about 0.1MPa m^1/2E.g. not less than about 0.5MPa m^1/2. The fiber-reinforced composite material may have a fracture toughness of not less than about 10MPa m^1/2E.g. not less than about 20MPa m^1/2。

It is to be understood that the term "fracture toughness" refers to the stress intensity factor at which a thin crack in a material begins to grow at mode I crack opening (i.e., at normal tensile stress applied perpendicular to the crack). Fracture toughness can be measured using the charpy impact test.

The malleable polymeric material may be soft. The fibre-reinforced composite material may be stiff. The ductile polymeric material may be softer (i.e., less hard) than the fiber-reinforced composite material. According to ASTM D2240, the ductile polymeric material may have a shore a hardness of no greater than about 95, such as no greater than about 90. According to ASTM D2240, the ductile polymeric material may have a shore a hardness of not less than about 50, for example not less than about 55. The ductile polymeric material may have a shore a hardness of about 60 to about 90. The malleable polymeric material may have a shore a hardness of about 80. The barcol hardness of the fiber-reinforced composite material may be not less than about 50 according to ASTM D2583.

It will be appreciated that the mechanical properties of the fibre-reinforced composite material (including tensile and shear modulus, elongation to failure, tensile strength, yield strength, fracture toughness and hardness) may be anisotropic, that is, the mechanical properties of the fibre-reinforced composite material may differ when measured along different axes. The anisotropy of mechanical properties in the fiber-reinforced composite may be due to an asymmetric arrangement of the reinforcing fibers in the composite.

A laminate or sub-laminate of fibre-reinforced composite material may comprise a plurality of layers of reinforcing fibre sheets arranged (i.e. embedded) in a laminated structure within a matrix material. The mechanical property anisotropy of the fiber reinforced composite laminate or sub-laminate may be due to (a) asymmetry caused by the arrangement of the reinforcement fiber plies forming the laminate or sub-laminate structure and/or (b) asymmetry caused by the orientation of the reinforcement fibers in the individual plies. In particular, within each individual ply, the reinforcing fibers may be substantially aligned along a single direction (i.e., "unidirectional" plies), or they may be randomly oriented relative to one another in the plane of the plies. In addition, within each laminate or sub-laminate, different plies may include reinforcing fibers aligned in different directions. For example, a laminate or sub-laminate may include one or more plies in which the reinforcing fibers are aligned in a first direction (referred to as a 0 ° orientation) and one or more plies in which the reinforcing fibers are aligned in a second direction (referred to as a 90 ° orientation) substantially perpendicular to the first direction. Additionally or alternatively, the laminate or sub-laminate may comprise plies arranged in a 30 °, 45 ° and/or 60 ° orientation, for example. By combining multiple plies having different orientations to form a single laminate or sub-laminate, the in-plane mechanical properties of the laminate or sub-laminate can be made effectively isotropic (although the out-of-plane mechanical properties perpendicular to the plies, i.e. in the direction of stacking of the plies, can be different from the in-plane properties).

Unless otherwise indicated, throughout the description and the appended claims, reference to tensile and shear modulus, tensile strength, elongation at failure and yield strength of a fibre-reinforced composite or a laminate or sub-laminate comprising a fibre-reinforced composite refers to said mechanical properties measured in-plane, i.e. in the plane in which the individual layers of reinforcing fibre lie or parallel to this plane. Conversely, unless otherwise specified, reference to the fracture toughness and stiffness of a fiber-reinforced composite or a laminate or sub-laminate comprising a fiber-reinforced composite refers to said mechanical properties measured out-of-plane, i.e. perpendicular to the plane of the individual plies.

Some fiber reinforced composite laminates or sub-laminates have anisotropic in-plane mechanical properties (e.g., unidirectional laminates or sub-laminates in which most or all of the layers of reinforcing fiber sheets are aligned along a single reinforcing fiber axis). Accordingly, unless otherwise specified, reference to tensile and shear moduli, tensile strength and yield strength of a fiber-reinforced composite or a laminate or sub-laminate comprising a fiber-reinforced composite refers to the minimum of the in-plane mechanical properties of the fiber-reinforced composite or a laminate or sub-laminate comprising a fiber-reinforced composite, for example, when measured in a range of in-plane orientations (e.g., 0 °, 45 ° and 90 ° to the reinforcing fiber axis). Similarly, unless otherwise specified, reference to the elongation to failure of a fiber reinforced composite or a laminate or sub-laminate comprising a fiber reinforced composite refers to the maximum value of the elongation to failure in that plane of the fiber reinforced composite or a laminate or sub-laminate comprising a fiber reinforced composite, for example, when measured in a range of in-plane orientations (e.g., 0 °, 45 °, and 90 ° to the reinforcing fiber axis).

The fibre-reinforced composite material may be manufactured by curing a matrix material in which layers of reinforcing fibres are embedded. The ductile polymeric material may not be susceptible to degradation (i.e., not degraded) during the curing process.

Curing the matrix material may require heating the matrix material to a curing temperature. The ductile polymeric material may not readily degrade (i.e., not degrade) at the curing temperature of the matrix material. The ductile polymeric material may be less susceptible to thermal degradation (i.e., not degraded) at temperatures of 300 ℃ or less, for example, at temperatures of 250 ℃ or less, or 200 ℃ or less, or 180 ℃ or less.

The ductile polymeric material may be stable (e.g., chemically and/or physically stable) at the curing temperature of the matrix material. The ductile polymeric material may be stable (e.g., chemically and/or physically stable) at a temperature of 300 ℃ or less, such as at a temperature of 250 ℃ or less, or at a temperature of 200 ℃ or less, or at a temperature of 180 ℃ or less.

The ductile polymeric material may include (e.g., consist of): one or more thermoplastic polymers. The ductile polymeric material may be thermoplastic. The ductile polymeric material may have a melting temperature that is higher than the solidification temperature of the matrix material. The melting temperature of the ductile polymeric material may be above 180 ℃, such as above 200 ℃, or above 250 ℃, or above 300 ℃.

The ductile polymeric material may have a glass transition temperature that is higher than the curing temperature of the matrix material. The ductile polymeric material may have a glass transition temperature of greater than 180 ℃, such as greater than 200 ℃, or greater than 250 ℃, or greater than 300 ℃.

The ductile polymeric material may include (e.g., consist of): one or more thermosetting polymers. The ductile polymeric material may be thermosetting (e.g., thermoset). The degradation temperature of the ductile polymeric material may be higher than the curing temperature of the matrix material. The degradation temperature of the ductile polymeric material may be above 180 ℃, such as above 200 ℃, or above 250 ℃, or above 300 ℃.

The ductile polymeric material may be comprised of one polymer. The ductile polymeric material may comprise (e.g., consist of) more than one polymer, such as a blend of polymers. The ductile polymeric material may include (e.g., consist of) one or more copolymers, such as one or more block copolymers.

The ductile polymeric material may include one or more additives. The ductile polymeric material may include one or more stabilizers, such as one or more co-stabilizers. For example, the malleable polymeric material may include one or more of the following: plasticizers, reinforcing agents, flame retardants, antioxidants, antiozonants, acid scavengers, light stabilizers (e.g., ultraviolet absorbers). The ductile polymeric material may include one or more fillers, such as one or more mineral fillers.

The ductile polymeric material may consist essentially of a polymer, for example, the ductile polymeric material has a polymer content of greater than 90 wt.%, or greater than 95 wt.%, or greater than 99 wt.%. The ductile polymeric material may be comprised entirely of a polymer.

The ductile polymeric material may include one or more polymers containing urethane (i.e., urethane) groups. The malleable polymeric material may include (e.g., consist of) polyurethane.

Additionally or alternatively, the ductile polymeric material may include one or more polymers formed in the reaction of a phenolic acid (i.e., phenol) or substituted phenolic acid (i.e., substituted phenol) with formaldehyde (i.e., methylal). For example, the ductile polymeric material may include (e.g., consist of): phenolic polymers, such as phenolic resins (also known as phenol formaldehyde resins). The ductile polymeric material may include (e.g., consist of): phenolic resins (i.e., phenol-formaldehyde resins) wherein the molar ratio of formaldehyde to phenol is less than 1. The ductile polymeric material may include (e.g., consist of): a novolak-type polymer.

The ductile polymeric material may include: one or more polymers containing urea (i.e., urea) groups. The ductile polymeric material may include (e.g., consist of): polyurea.

The ductile polymeric material may include one or more toughening polymers, such as a toughening binder. The toughening adhesive can be toughening polyurethane, toughening phenolic resin, toughening acrylonitrile butadiene or toughening epoxy resin.

Toughened adhesives may be produced by adding diluents, acrylates or plasticizers to the adhesive. Toughened adhesives may be produced by adding a second phase (such as thermoplastic or rubber particles) to an epoxy resin matrix. Toughened adhesives may be produced by adding polyurethane segments to an adhesive polymer matrix.

The ductile polymeric material may include a polymer matrix in which thermoplastic particles, glass microspheres, or polymer microspheres are dispersed. The polymer matrix may be a thermoset polymer matrix, such as an epoxy resin.

The fibre-reinforced composite material may be a fibre-reinforced polymer, i.e. the matrix material of the fibre-reinforced composite material may be a polymer. The matrix material of the fibre-reinforced composite material may be a thermosetting polymer (i.e. thermoset).

The fiber-reinforced composite may include carbon reinforcing fibers. For example, the carbon reinforcing fibers may be Polyacrylonitrile (PAN) -based carbon fibers, such asIM7 fiber. The fibre-reinforced composite material may be a Carbon Fibre Reinforced Polymer (CFRP). The fibre-reinforced composite material may comprise resin-bonded unidirectional carbon fibre plies.

The fiber-reinforced composite may include aramid (i.e., aramid) reinforcing fibers. The fiber-reinforced composite may include para-aramid reinforcing fibers. For example, the fiber-reinforced composite may comprise a fiber reinforced composite made from poly (p-phenylene terephthalamide)Or p-phenylene terephthalamideThe formed reinforcing fibers.

The fiber-reinforced composite may include reinforcing fibers formed from a thermoset liquid crystal polyoxazole. For example, the fiber-reinforced composite material may include a fiber-reinforced composite material composed of poly (p-phenylene-2, 6-benzobisoxazole)The formed reinforcing fibers.

The matrix material may comprise (e.g. consist of) one or more of the following: epoxy resins (i.e., cured epoxy resins), polyesters, vinyl esters, polyamides (e.g., aliphatic or semi-aromatic polyamides, such as nylon).

Only two sub-laminates of the fiber-reinforced composite may be spaced apart from each other by the ductile polymeric material. Alternatively, two or more sub-laminates of the fibre-reinforced composite material may be spaced apart from each other by the ductile polymeric material. At least three, for example at least four, or at least five, sub-laminates of the fiber-reinforced composite material may be spaced apart from each other by the ductile polymeric material.

Two or more sub-laminates of fibre reinforced composite material may be spaced apart from each other by one or more layers of ductile polymeric material.

Each of the two or more sub-laminates of the fiber-reinforced composite may be separated from each adjacent sub-laminate of the fiber-reinforced composite by a layer (e.g., only one) of the ductile polymeric material. Each of the two or more sub-laminates of the fiber-reinforced composite may be spaced apart from each adjacent sub-laminate of the fiber-reinforced composite by a (e.g. only one) solid layer of the ductile polymeric material. Each (e.g., solid) layer of malleable polymeric material may be monolithic, that is, substantially structurally and/or chemically continuous.

The malleable polymeric material may not be a foam. The malleable polymeric material may not have a cellular (e.g., open or closed cell) structure, i.e., the malleable polymeric material may be a non-cellular material. The ductile polymeric material may not be fiber reinforced, i.e., the ductile polymeric material may be unreinforced. Two or more sub-laminates of fiber reinforced composite material may be spaced apart from each other by one or more solid layers of non-reinforced ductile polymeric material.

Two or more sub-laminates of fiber reinforced composite material and one or more layers of ductile polymeric material may be arranged (e.g., stacked) in alternating (i.e., in a laminar manner) radial directions substantially perpendicular to the longitudinal axis of the structural support shell (i.e., to form a laminate).

Two or more sub-laminates and the ductile polymeric material may be bonded to each other. The two or more sub-laminates and the ductile polymeric material may be bonded to each other by an adhesive. Alternatively, two or more sub-laminates and the ductile polymeric material may be bonded to each other without the use of an adhesive. For example, during the manufacture of the structural support shell, a bond may be formed between the two or more sub-laminates and the ductile polymeric material when the preform is cured.

The structural support shell may enclose one or more fan liners. The structural support shell may be a structural support shell for enclosing one or more fan liners, for example a structural support shell configured to enclose one or more fan liners. The structural support shell may support one or more fan liners. The structural support housing may be a structural support housing for supporting one or more fan liners, for example a structural support housing configured to support one or more fan liners. The one or more fan liners may include (e.g., be) one or more impingement liners. The one or more fan liners may include (e.g., be) one or more acoustic liners. One or more fan liners may be disposed inside the structural support case (e.g., mounted to an inside surface of the structural support case that faces the fan blades when used in a gas turbine engine).

The at least one region in which the two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by the ductile polymeric material may extend around at least about 10%, such as at least about 25%, or at least about 50% of the perimeter of the structural support shell. The at least one region in which the two or more sub-laminates of fibre reinforced composite material are spaced apart from each other by the ductile polymeric material may extend around a majority of the perimeter of the structural support shell, for example the entire perimeter. At least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may extend longitudinally along at least about 5%, such as at least about 10%, or at least about 20%, or at least about 30%, or at least about 40%, or at least about 50% of the length of the structural support shell. At least one region in which two or more sub-laminates of fibre reinforced composite material are spaced apart from one another by a ductile polymeric material may extend longitudinally along a majority of the length, for example the entire length, of the structural support shell. At least one region in which two or more sub-laminates of fiber reinforced composites are spaced apart from each other by a ductile polymeric material may form at least about 1%, such as at least about 5%, or at least about 10%, or at least about 15%, or at least about 20%, or at least about 25%, or at least about 30%, or at least about 35%, or at least about 40%, or at least about 45%, or at least about 50% of the radial thickness of the structural support shell (i.e., the radial thickness of the structural support shell in the vicinity of the at least one region). At least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may form a majority of the radial thickness of the structural support shell (i.e., the radial thickness of the structural support shell in the vicinity of the at least one region), such as the entire radial thickness.

At least one region in which two or more sub-laminates of fibre-reinforced composite material are spaced apart from each other by a ductile polymeric material may itself be surrounded by fibre-reinforced composite material. At least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may be embedded in a larger region of the fiber reinforced composite material. For example, most structural support shells may be formed from fiber reinforced composite materials. Most (e.g., monolithic) structural support shells may be formed of a fiber-reinforced composite material, except for at least one region in which two or more sub-laminates of the fiber-reinforced composite material are spaced apart from one another by a ductile polymeric material. The fiber-reinforced composite material present in the at least one region in which the two or more sub-laminates of fiber-reinforced composite material are spaced apart from each other by the ductile polymeric material may be continuous with (i.e., extend continuously into) the fiber-reinforced composite material surrounding the at least one region. The two or more sub-laminates of fiber reinforced composite material may be continuous with (e.g., extend continuously into) the fiber reinforced composite material surrounding the at least one region. The two or more sub-laminates of fibre reinforced composite material may be continuous with (e.g. extend continuously into) the larger fibre reinforced composite laminate structure surrounding the at least one region.

The structural support shell may comprise a single zone in which two or more sub-laminates of fibre reinforced composite material are spaced apart from each other by a ductile polymeric material.

The structural support shell may comprise two or more zones, for example three or more zones, or four or more zones, or five or more zones, in which two or more sub-laminates of fibre reinforced composite material are spaced apart from each other by the ductile polymeric material. Two or more regions, such as three or more regions, or four or more regions, or at least two (e.g., each) of five or more regions, may be spaced apart from each other. At least two (e.g., each) of the regions may be spaced apart from one another around a perimeter of the structural support shell. At least two (e.g., each) of the regions may be spaced apart from each other along a length of the structural support shell. At least two (e.g., each) of the regions may be spaced apart from each other in a radial direction, i.e., a radial thickness of the structural support shell (e.g., proximate to the two or more regions). At least two (e.g., each) of the regions that are spaced apart from each other may be spaced apart from each other by the fiber-reinforced composite material. At least two (e.g., each) of the regions that are spaced apart from each other may be spaced apart from each other by regions that engage the fiber-reinforced composite material. The fibre-reinforced composite material present in at least two (e.g. each) of said regions that are spaced apart from each other may be continuous with the fibre-reinforced composite material in the joint region. Two or more zones, for example three or more zones, or four or more zones, or five or more zones, in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may partially overlap each other. For example, the regions may be spaced apart from each other in the radial direction but at least partially overlap around the perimeter of the structural support shell and/or along the length thereof.

The thickness (i.e. in the radial direction) of the ductile polymeric material disposed between each adjacent pair of sub-laminates of the fiber reinforced composite material may be no greater than the thickness (i.e. in the radial direction) of any of the two or more sub-laminates of the fiber reinforced composite material. For example, the maximum thickness (i.e., in the radial direction) of one or more layers of the ductile polymeric material may be no greater than the thickness of any one of the two or more sub-laminates of the fiber reinforced composite material (i.e., in the radial direction). The thickness (i.e. in the radial direction) of (e.g. one or more layers of) the ductile polymeric material may be no more than about 50% of the thickness (i.e. in the radial direction) of any of the two or more sub-laminates of the fiber-reinforced composite material.

The thickness of the ductile polymeric material (e.g., each of the one or more layers of ductile polymeric material) disposed between each adjacent pair of two or more sub-laminates of the fiber reinforced composite may be not greater than about 2.0mm, such as not greater than about 1.5mm, or not greater than about 1.0mm, or not greater than about 0.8mm, or not greater than about 0.6mm, or not greater than about 0.4mm, or not greater than about 0.3 mm. The thickness of the ductile polymeric material (e.g., each of the one or more layers of ductile polymeric material) disposed between each adjacent pair of two or more sub-laminates of the fiber reinforced composite may be about 0.05mm to about 1.00 mm. The thickness of the ductile polymeric material (e.g., each of the one or more layers of ductile polymeric material) disposed between each adjacent pair of two or more sub-laminates of the fiber reinforced composite may be about 0.1mm to about 0.5 mm. The thickness of the ductile polymeric material (e.g., each of the one or more layers of ductile polymeric material) disposed between each adjacent pair of two or more sub-laminates of the fiber reinforced composite may be about 0.6 mm.

Each sub-laminate of the fiber-reinforced composite may include layers of reinforcing fiber sheets having a thickness of no greater than about 15mm, such as no greater than about 10.0mm, or no greater than about 8.0mm, or no greater than about 6.0mm, or no greater than about 4.0mm, or no greater than 1.0mm, or no greater than about 0.8mm, or no greater than about 0.6mm, or no greater than about 0.4mm, or no greater than about 0.3 mm.

Each sub-laminate of the fibre-reinforced composite material may comprise at least two, for example at least three, or at least four, or at least five, plies of reinforcing fibres. The thickness of each sub-laminate of the fibre-reinforced composite material may be not less than about 0.6mm, for example not less than about 0.8mm, or not less than about 1.0mm, or not less than about 1.2mm, or not less than about 1.4mm, or not less than about 1.6mm, or not less than about 1.8mm, or not less than about 2.0 mm. The thickness of each sub-laminate of the fiber reinforced composite may be no greater than about 15.0mm, such as no greater than about 10.0mm, or no greater than about 8.0mm, or no greater than about 6.0mm, or no greater than about 4.0 mm.

Each layer of the ductile polymeric material may be thinner than each sub-laminate of the fiber-reinforced composite material. The thickness of each layer of the ductile polymeric material may be no greater than 80% of the thickness of any of the sub-laminates of the fiber reinforced composite, such as no greater than 70% of the thickness of any of the sub-laminates of the fiber reinforced composite, or no greater than 60% of the thickness of any of the sub-laminates of the fiber reinforced composite, or no greater than 50% of the thickness of any of the sub-laminates of the fiber reinforced composite, or no greater than 40% of the thickness of any of the sub-laminates of the fiber reinforced composite, or no greater than 30% of the thickness of any of the sub-laminates of the fiber reinforced composite, or no greater than 20% of the thickness of any of the sub-laminates of the fiber reinforced composite.

The ductile polymeric material may have a density of no greater than about 2g/cm³E.g., not greater than about 1.8g/cm³Or not greater than about 1.6g/cm³. The ductile polymeric material may have a density of about 1.0g/cm³To about 2.0g/cm³. The ductile polymeric material may have a density of about 1.6g/cm³。

The structural support housing may include a forward portion, a middle portion, and a rearward portion along its axial extent. The anterior portion and the posterior portion may be thinner than the central portion. The thickness of each of the anterior portion and the posterior portion may decrease with distance away from the intermediate portion. Two or more sub-laminates of fiber reinforced composite material may be positioned in the intermediate portion at least one region in which the regions are spaced apart from each other by the ductile polymeric material. At least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may be selectively positioned in a portion of a structural support housing configured to enclose a fan. At least one region in which two or more sub-laminates of fiber reinforced composite material are spaced apart from each other by a ductile polymeric material may be selectively positioned in an intended path of fan blade shedding. The at least one region in which the two or more sub-laminates of the fiber reinforced composite are spaced apart from each other by the ductile polymeric material may be at least one impact region, i.e., at least one impact region that may be most impacted by the fan blade during an FBO event. The at least one impingement region may be a region 10 degrees forward or aft of a location where a plane of center of gravity of the fan intersects the centerline of the engine.

One, for example two, of the two or more sub-laminates of fibre reinforced composite material may form a surface of the structural support shell, for example an outer side surface or an inner side surface.

According to a second aspect, there is provided a gas turbine engine comprising a structural support casing according to the first aspect. The structural support shell may surround (e.g., support) a fan liner, such as a fan impingement liner and/or an acoustic liner. The structural support housing may enclose the fan.

According to a third aspect, there is provided a method of laying down a preform for a structural support shell housing fan blades in a gas turbine engine, the method comprising: applying a first fiber reinforced composite sub-laminate to a tool; applying a ductile polymeric material to the first fiber reinforced composite sub-laminate; and applying a second fiber reinforced composite sub-laminate to the ductile polymeric material.

The preform may be a preform for the entire structural support shell. The preform may be a preform for a portion of a structural support shell. The structural support housing may be a fan containment housing (e.g., a fan containment housing), such as a hard-walled fan containment housing (e.g., a hard-walled fan containment housing). The preform may be an uncured preform. Both the first and second fiber reinforced composite sub-laminates may be uncured fiber reinforced composite sub-laminates. The tool may be a mandrel.

Applying the first fiber reinforced composite sub-laminate to the tool may comprise (e.g., consist of): one or more, for example two or more, or three or more, or four or more, plies of reinforcing fibers are applied to the tool. Applying the first fiber reinforced composite sub-laminate to the tool may comprise (e.g., consist of): one or more, for example two or more, or three or more, or four or more, plies of reinforcing fibers are stacked one above the other on the tool. One or more, for example two or more, or three or more, or four or more, plies of reinforcing fibers may be applied individually to the tool. Alternatively, a plurality (e.g., two or more, three or more, or four or more) of the reinforcement fiber plies may be applied together (i.e., simultaneously) to the tool. One or more plies of reinforcing fibers, such as two or more, or three or more, or four or more plies of reinforcing fibers, may be impregnated with uncured matrix material and/or one or more precursors of matrix material, i.e., the layers of reinforcing fibers may be "pre-impregnated" plies of reinforcing fibers. One or more sheets of reinforcing fibers may be provided in the form of a strip of reinforcing fibers, such as two or more, or three or more, or four or more sheets of reinforcing fibers. The reinforcing fibre tapes may be impregnated with uncured matrix material and/or one or more precursors of matrix material, i.e. the reinforcing fibre tapes may be "pre-impregnated" reinforcing fibre tapes. Alternatively, the matrix material may be injected into the preform after the reinforcing fiber plies have been applied.

Applying the ductile polymeric material to the first fiber reinforced composite sub-laminate may include applying a ply of ductile polymeric material to the first fiber reinforced composite sub-laminate. Alternatively, applying the ductile polymeric material to the first fiber reinforced composite sub-laminate may include applying a tape of ductile polymeric material to the first fiber reinforced composite sub-laminate. Alternatively, applying the ductile polymeric material onto the first fiber reinforced composite sub-laminate may include spray applying a film of the ductile polymeric material onto the first fiber reinforced composite sub-laminate.

Applying the second fiber-reinforced composite sub-laminate to the ductile polymeric material may include (e.g., consist of): one or more, for example two or more, or three or more, or four or more, plies of reinforcing fibers are applied to the ductile polymeric material. Applying the second fiber-reinforced composite sub-laminate to the ductile polymeric material may include (e.g., consist of): one or more, for example two or more, or three or more, or four or more, plies of reinforcing fibers are stacked one above the other on the ductile polymeric material. One or more, such as two or more, or three or more, or four or more, plies of reinforcing fibers may be individually applied to the ductile polymeric material. Alternatively, a plurality (e.g., two or more, three or more, or four or more) of the reinforcement fiber plies may be applied together (i.e., simultaneously) onto the ductile polymeric material. One or more plies of reinforcing fibers, such as two or more, or three or more, or four or more plies of reinforcing fibers, may be impregnated with uncured matrix material and/or one or more precursors of matrix material, i.e., the layers of reinforcing fibers may be "pre-impregnated" plies of reinforcing fibers. One or more sheets of reinforcing fibers may be provided in the form of a strip of reinforcing fibers, such as two or more, or three or more, or four or more sheets of reinforcing fibers. The reinforcing fibre tapes may be impregnated with uncured matrix material and/or one or more precursors of matrix material, i.e. the reinforcing fibre tapes may be "pre-impregnated" reinforcing fibre tapes. Alternatively, the matrix material may be injected into the preform after the reinforcing fiber plies have been applied.

The steps of applying the ductile polymeric material and applying the fiber-reinforced composite sub-laminate may be repeated to build a preform comprising three or more, for example four or more, or five or more, sub-laminates of fiber-reinforced composite material spaced apart from each other by the ductile polymeric material. For example, the method may include applying a first fiber reinforced composite sub-laminate to a tool; applying a ductile polymeric material to the first fiber reinforced composite sub-laminate; applying a second fiber-reinforced composite sub-laminate to the ductile polymeric material; applying a ductile polymeric material onto the second fiber reinforced composite sub-laminate; and applying a third fiber reinforced composite sub-laminate to the ductile polymeric material disposed on the second fiber reinforced composite sub-laminate.

The malleable polymeric material may consist of one polymer, or the malleable polymeric material may include more than one polymer, for example the malleable polymeric material may be a blend of polymers. The ductile polymeric material may comprise one or more additives or stabilizers, for example, selected from the group consisting of: plasticizers, reinforcing agents, flame retardants, antioxidants, antiozonants, acid scavengers, light stabilizers (e.g., ultraviolet absorbers). The ductile polymeric material may include one or more fillers, such as one or more mineral fillers. The malleable polymeric material may include one or more polymers containing urethane (i.e., urethane) groups, such as polyurethane. The malleable polymeric material may include one or more polymers formed in the reaction of a phenolic acid (i.e., phenol) or substituted phenolic acid (i.e., substituted phenol) with formaldehyde (i.e., methylal), such as a phenolic polymer or phenolic resin (also referred to as a phenol formaldehyde resin).

The fibre-reinforced composite material may be a fibre-reinforced polymer, i.e. the (i.e. cured) matrix material of the fibre-reinforced composite material may be a polymer. The matrix material of the fibre-reinforced composite material may be a thermosetting polymer (i.e. thermoset). The uncured matrix material may include one or more of the following: epoxy resin, polyester resin, polyimide resin, silicone resin, benzoxazine resin, bismaleimide resin, cyanate ester resin, vinyl ester resin, phenol resin, polyurethane resin. The uncured matrix material may include one or more catalysts or initiators. The cured matrix material may include one or more of the following: epoxy resins (i.e., cured epoxy resins), polyesters, polyimides, polysiloxanes, vinyl esters, polyamides, polyurethanes, polybenzoxazines, bismaleimides, cyanate esters.

The fiber-reinforced composite may include carbon reinforcing fibers. The fibre-reinforced composite material may be a Carbon Fibre Reinforced Polymer (CFRP). The fiber-reinforced composite may include aramid (i.e., aramid) reinforcing fibers. The fiber-reinforced composite may include para-aramid reinforcing fibers. For example, the fiber-reinforced composite may comprise a fiber reinforced composite made from poly (p-phenylene terephthalamide)Or p-phenylene terephthalamideThe formed reinforcing fibers. The fiber-reinforced composite may include reinforcing fibers formed from a thermoset liquid crystal polyoxazole. For example, the fiber-reinforced composite material may include a fiber-reinforced composite material composed of poly (p-phenylene-2, 6-benzobisoxazole)The formed reinforcing fibers.

According to a fourth aspect, there is provided a method of manufacturing a structural support case for housing fan blades in a gas turbine engine, the method comprising: laying down a preform for a structural support shell by a method according to the third aspect; and curing the preform.

Curing the preform may include heating the preform. Curing the preform may include heating the preform to a temperature of no greater than 300 ℃, such as no greater than 250 ℃, or no greater than 200 ℃, or no greater than 180 ℃. Curing the preform may include heating the preform to a temperature of not less than 100 ℃, for example not less than 150 ℃.

Additionally or alternatively, curing the preform may include applying pressure to the preform.

The method may further comprise forming or shaping the preform prior to curing and/or forming or shaping the structural support shell after curing.

According to a fifth aspect, there is provided a Carbon Fiber Reinforced Polymer (CFRP) composite structural support shell for housing fan blades in a gas turbine engine, the CFRP composite structural support shell comprising at least one region in which two or more CFRP sub-laminates are spaced apart from one another by polyurethane and/or phenolic resin having an elongation to failure of at least about 50%, such as at least about 100%, and/or a tensile modulus of no greater than about 10GPa, such as no greater than about 5 GPa. The thickness of the polyurethane and/or phenolic resin provided between each adjacent pair of two or more CFRP sub-laminates may be no greater than about 2.0mm, such as no greater than about 1.0 mm.

According to a sixth aspect, there is provided a Carbon Fiber Reinforced Polymer (CFRP) composite structural support shell for housing fan blades in a gas turbine engine, the CFRP composite structural support shell comprising at least one region in which two or more CFRP sub-laminates are spaced apart from each other by a polyurea and/or toughening binder and/or a polymer matrix comprising thermoplastic particles, glass microspheres or polymer microspheres, the polyurea and/or toughening binder and/or the polymer matrix comprising thermoplastic particles, glass microspheres or polymer microspheres having at least about 1MPa/m³E.g. at least about 5MPa/m³And/or a tensile modulus of not greater than about 5GPa, such as not greater than about 1 GPa. The polyurea and/or toughening adhesive and/or the polymer matrix including thermoplastic particles, glass microspheres, or polymer microspheres disposed between each adjacent pair of two or more CFRP sub-laminates may have a thickness of no greater than about 1mm, such as no greater than about 0.5 mm.

It will be understood by those skilled in the art that features described in relation to any one of the above aspects may be applied to any other aspect, mutatis mutandis, unless mutually exclusive. Furthermore, any feature described herein may be applied to any aspect and/or in combination with any other feature described herein, unless mutually exclusive.

Drawings

Embodiments will now be described, by way of example only, with reference to the accompanying drawings, in which:

FIG. 1 is a cross-sectional side view of a gas turbine engine;

FIG. 2 is a cross-sectional side view of the fan containment case;

FIG. 3 is a schematic cross-sectional view through a portion of a fan containment case;

FIG. 4 is a schematic illustration of a shear force distribution through a portion of a fan containment case;

FIG. 5 is a graph of the energy absorbed under the impact of a fan blade for three example materials;

FIG. 6 is a force-displacement graph of a carbon fiber and ductile polymer composite; and

fig. 7 is a flowchart of a method of manufacturing a fan receiving case.

Detailed Description

Referring to FIG. 1, a gas turbine engine is generally indicated at 10 having a primary and rotational axis 11. Engine 10 includes, in axial-flow series order, an air intake 12, a propulsion fan 13, an intermediate pressure compressor 14, a high pressure compressor 15, a combustion apparatus 16, a high pressure turbine 17, an intermediate pressure turbine 18, a low pressure turbine 19, and an exhaust nozzle 20. Nacelle 21 generally surrounds engine 10 and defines both air intake 12 and exhaust nozzle 20. A fan containment case 22 extends around the fan 13 inside the nacelle 21.

The gas turbine engine 10 operates in a conventional manner such that air entering the air intake 12 is accelerated by the fan 13 to produce two air streams: a first air flow into the intermediate pressure compressor 14 and a second air flow through the bypass duct 23 to provide propulsion. The medium pressure compressor 14 compresses the air stream directed therein before delivering the air to the high pressure compressor 15 where it is further compressed.

The compressed air discharged from the high-pressure compressor 15 is led into a combustion device 16, where the compressed air is mixed with fuel and the mixture is combusted. The resulting hot combustion products are then expanded through and thereby drive the high pressure turbine 17, the intermediate pressure turbine 18, and the low pressure turbine 19 before being discharged through the nozzle 20 to provide additional propulsive force. The high pressure turbine 17, the intermediate pressure turbine 18 and the low pressure turbine 19 each drive the high pressure compressor 15, the intermediate pressure compressor 14 and the fan 13, respectively, by means of suitable interconnecting shafts.

Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. For example, such engines may have an alternative number of interconnecting shafts (e.g., two) and/or an alternative number of compressors and/or turbines. Further, the engine may include a gearbox disposed in the drive train from the turbine to the compressor and/or the fan.

The structure of the fan containment case 22 is shown in more detail in fig. 2, which shows a cross-sectional view of a portion of the fan containment case. The fan receiving case 22 includes an intermediate portion (barrel portion) 23 extending between a front portion 24 and a rear portion 25. The fan containment case 22 is formed primarily of a fiber reinforced composite material and is positioned around the fan 13.

The fan impingement liner 26 is adhered to the inside surface of the intermediate portion 23 of the fan containment case 22. The fan impingement liner 26 is constructed of layers of fiber reinforced composite and honeycomb materials and is designed to absorb a significant amount of energy upon impact of the blade during a Fan Blade Out (FBO) event. An abradable layer 27 composed of a honeycomb material is adhered to the fan impingement liner 26. A front acoustic liner 28 and a rear acoustic liner 29 are adhered to the fan containment case 22 proximate the forward portion 24 and the aft portion 25, respectively. The fan containment case 22 serves as a rigid structural support for the fan impingement liner 26, abradable layer 27, and acoustic liners 28 and 29.

The internal structure of the impingement portion 30 of the intermediate portion 23 of the fan containment case 22 is shown in greater detail in fig. 3. This portion 30 of fan containment case 22 is formed from alternating sub-laminate layers of Carbon Fiber Reinforced Polymer (CFRP) material 31, 32 and 33, for example, spaced apart from one another by layers of ductile polymeric material 34 and 35 (e.g., polyurethane or phenolic resin). The layers of ductile polymeric materials 34 and 35 are bonded directly to the CFRP sub-laminate to provide a laminate structure. The layer of ductile polymeric material is typically much thinner than the CFRP sub-laminate. For example, the layer of ductile polymeric material may be about 0.5mm thick, while each CFRP sub-laminate may be about 3.0mm thick. Although the CFRP material comprises unidirectional carbon fiber plies bonded to each other in a resin matrix, it should be understood that the CFRP material may be replaced by any fiber reinforced composite material deemed suitable for use by those skilled in the art. The malleable polymeric layer is a solid polymer film.

The impingement portion 30 extends angularly completely around the engine (i.e., completely around the perimeter of the fan containment case 22) in an area of the fan containment case 22 proximate the fan. The remainder of the fan containment case 22 may be formed of a CFRP material without a layer of ductile polymeric material, however the structure of the impingement portion 30 may also be repeated in other areas, such as throughout the fan containment case.

The impact portion 30 is structured to absorb a significant amount of energy from the impacting fan blade during an FBO event. In particular, malleable polymeric materials like polyurethane or phenolic resin are significantly more malleable and flexible than fiber reinforced materials like CFRP. For example, ductile polymeric materials like polyurethane or phenolic resins generally have a significantly higher elongation to failure and a significantly lower modulus of elasticity (particularly tensile modulus of elasticity) than fibrous reinforcements like CFRP. Accordingly, under the impact of the fan blade during an FBO event, the ductile polymeric material layer in the impact portion of the fan containment case is able to undergo substantially more elastic and plastic deformation than the sub-laminate of the CFRP. This means that on impact the ductile polymeric layer is effectively independent of the CFRP sub laminate and there is little shear stress transfer between the adjacent ductile polymeric layer and the CFRP sub laminate.

This effect is illustrated in fig. 4, which shows that an impact occurring at point I on the inside surface causes the shear stress distribution schematically shown at D1, D2, and D3 of sub-laminates 31, 32, and 33, and the minimum stress supported by ductile polymeric layers 34 and 35. The resultant compressive stress experienced by the CRFP sub-laminate 33 on the inside of the impact portion (indicated by arrow 37 at point I) and the tensile stress experienced by the CFRP sub-laminate 31 on the outside of the impact portion (indicated by arrow 38 at point O) are greatly reduced compared to the compressive and tensile stresses experienced in the absence of the ductile polymeric layer. This reduces the likelihood that the ultimate tensile or compressive strength of the carbon fibers in the CFRP sub-laminate will be reached, thus reducing the likelihood of brittle failure of the CFRP sub-laminate.

By including a layer of ductile polymeric material, the CFRP sub-laminate can achieve greater bending before failure than can be achieved using a unitary flat sheet of CFRP material. Effectively, the ductility of the CFRP laminate structure is increased by the layer comprising the ductile polymeric material. Thus, the impingement area of the fan containment case is able to absorb significantly more energy under the impingement of the fan blades. In addition, these ductile polymeric material layers first deform elastically upon impact and then deform plastically, rather than undergoing brittle failure, because propagation of cracks in the laminate structure is hindered by the presence of the ductile polymeric material layers.

Fig. 5 compares the amount of energy that can be absorbed at a test portion of a fan containment case including an impact region containing a ductile polymeric layer to a baseline amount of energy absorbed at a reference test portion of a pure CFRP fan containment case under the same impact conditions. In fig. 5, the amount of energy absorbed by the phenolic and polyurethane layers is expressed as a percentage relative to a normalized reference of 100%. The use of both phenolic and polyurethane layers causes an increase in the amount of energy absorbed. The ductile polymeric layer increases the amount of energy required to initiate a crack or initiate fiber failure in the laminate structure (referred to as "initiation energy"), both mechanisms resulting in a reduced load bearing capacity. In both examples, particularly the use of polyurethanes with higher elongation to failure results in a significant increase in the total amount of energy absorbed upon impact.

Fig. 6 shows force-displacement graphs measured for CFRP sub laminates spaced apart by polyurethane ductile polymeric material (dark gray) and for CFRP laminate structures lacking ductile polymeric material (light gray). By adding a ductile polymeric layer, the ductility of the laminate is significantly increased, as indicated by the increase in maximum displacement before yielding. The energy absorbed by the structure may be determined by the area under the force-displacement graph.

The fan containment case 22 may be manufactured using standard composite manufacturing techniques known in the art. For example, the fan housing case 22 may be manufactured by first laying a preform for the fan housing case and then curing the preform. Laying up a preform typically involves repeatedly applying carbon fiber plies in a laminar manner to a forming tool such as a mandrel. The carbon fibre plies may be applied in the form of carbon fibre tape, in particular pre-impregnated with an uncured matrix material such as uncured resin. Alternatively, the uncured matrix material may be injected into the preform after layup has been completed.

The impact region of the preform may be constructed by applying plies of the selected expandable polymeric material in the impact region rather than individual carbon fiber plies. The malleable polymeric material may also be provided in the form of a polymeric tape so that both the carbon fibers and the polymeric material may be laid using the same automated laying tool. For example, every fifth sheet of carbon fiber may be replaced by a laminate of ductile polymeric material in the impact zone.

The preform may be shaped or formed prior to curing using any composite forming or forming technique known in the art, for example to form a shaped forward portion and a rearward portion of the fan containment case.

After the laying and/or shaping or forming is completed, the preform is typically cured by heating to the curing temperature of the matrix material and/or applying pressure to the preform.

Fig. 7 is a flow chart illustrating a simplified method of manufacturing a fan containment case. At block 101, a first carbon fiber sheet layer impregnated with a matrix material is applied to a tool to form a first sub-laminate. At block 102, a ductile polymeric material is applied to a first sub-laminate. In block 103, a second carbon fiber sheet layer impregnated with a matrix material is applied to the ductile polymeric material to form a second sub-laminate, thereby forming a preform for the fan containment case. At block 104, the preform structure is cured, such as by applying heat and pressure.

It is to be understood that the present invention is not limited to the above-described embodiments, and various modifications and improvements may be made without departing from the concept described herein. Any feature may be used alone or in combination with any other feature or features unless mutually exclusive, and the disclosure extends to and includes all combinations and subcombinations of one or more features described herein.