阅读说明：本技术 复合翼型单体以及单体的相应组件 (Composite airfoil-shaped single body and corresponding assembly of single bodies ) 是由 莱斯利·路易斯·兰根布鲁纳 伊恩·弗朗西斯·普伦蒂斯 罗萨·李·内梅克 亚当·马克斯·瑞斯蒂 于 2017-07-11 设计创作，主要内容包括：一种复合翼型单体(40),包括翼型件(42),翼型件(42)从翼型件的基部(45)延伸至翼型件的尖端(46),并且在尖端一体地形成有不超过一个的外平台(50)和/或在基部一体地形成有不超过一个的内平台(54)。平行复合层(56)或编织纤维延伸穿过翼型件并穿过外平台和/或内平台。外弯曲部和/或内弯曲部(73、75)分别在外平台和/或内平台与翼型件之间延伸。组件包括复合翼型单体的圆形排(93),复合翼型单体的圆形排(93)从外罩或外壳(96)径向向内倚靠并且安装至外罩或外壳(96)上。外紧固件和/或内紧固件(76、78)可以分别将外平台和内平台固定至外罩或外壳以及内罩(60),并且包括柄(80),柄(80)从外紧固板和内紧固板(84)大致垂直地分别延伸穿过外平台和内平台中的平台孔(82)以及穿过外罩或外壳以及内罩中的外孔和内孔(83)。螺母(88)拧在柄的螺纹端(90)上。(A composite airfoil monolithic body (40) includes an airfoil (42), the airfoil (42) extending from a base (45) of the airfoil to a tip (46) of the airfoil and having no more than one outer platform (50) integrally formed at the tip and/or no more than one inner platform (54) integrally formed at the base. Parallel composite layers (56) or woven fibers extend through the airfoil and through the outer platform and/or the inner platform. Outer and/or inner bends (73, 75) extend between the outer and/or inner platforms and the airfoil, respectively. The assembly includes a circular row (93) of individual composite aerofoil units, the circular row (93) of individual composite aerofoil units depending radially inwardly from the shroud or casing (96) and being mounted to the shroud or casing (96). Outer and/or inner fasteners (76, 78) may secure the outer and inner platforms to the outer and inner shrouds (60), respectively, and include a shank (80) extending generally perpendicularly from the outer and inner fastening plates (84) through platform apertures (82) in the outer and inner platforms, respectively, and through outer and inner apertures (83) in the outer and inner shrouds, respectively. A nut (88) is threaded onto the threaded end (90) of the shank.)

1. A composite airfoil monomer, comprising:

an airfoil extending from a base to a tip of the airfoil, an

The airfoil is integrally formed with no more than one outer platform at the tip and/or no more than one inner platform at the base.

2. The monomer of claim 1, further comprising:

the airfoil extending longitudinally or radially from the base to the tip,

the outer platform extends laterally or circumferentially from the tip in a right-hand or clockwise direction, or in a left-hand or counterclockwise direction, and

the inner platform extends laterally or circumferentially from the base in the right-hand direction or the clockwise direction, or in the left-hand direction or the counter-clockwise direction.

3. The unitary body of claim 2, further comprising parallel composite layers or woven fibers extending through the airfoil and through the outer platform and/or the inner platform.

4. The unitary body of claim 3, further comprising an outer bend and/or an inner bend extending between the outer platform and/or the inner platform, respectively, and the airfoil.

5. The unitary body of claim 4, further comprising the outer bend and/or the inner bend, the outer bend and/or the inner bend being circular arc shaped and having an outer radius and/or an inner radius, respectively.

6. An assembly of composite airfoil monomers, comprising:

a circular row of composite airfoil monomers leaning radially inward from and mounted to a shroud or casing,

each of the airfoil cells including an airfoil extending radially from a base of the airfoil to a tip of the airfoil,

the airfoil integrally formed with no more than one outer platform at the tip and/or integrally formed with no more than one inner platform at the base,

the outer platform extends circumferentially from the tip in either a clockwise or counterclockwise direction, and

the inner platform extends circumferentially from the base in either the clockwise direction or the counterclockwise direction.

7. The assembly of claim 6, further comprising parallel composite layers or woven fibers extending through the airfoil and through the outer platform and/or the inner platform.

8. The assembly of claim 7, further comprising an outer bend and an inner bend extending between the outer platform and the inner platform, respectively, and the airfoil.

9. The assembly of claim 8, further comprising the outer bend and the inner bend, the outer bend and the inner bend being circular arc shaped and having an outer radius and an inner radius, respectively.

10. The assembly of claim 7, further comprising:

external and/or internal fasteners fixing the outer and inner platforms to the outer and inner shrouds,

the outer and inner fasteners include shanks extending substantially perpendicularly from outer and inner fastening plates through platform holes in the outer and inner platforms and through outer and inner holes in the outer or outer and inner shrouds, respectively, and

a nut threaded onto the threaded end of the shank.

11. The assembly of claim 10, further comprising an outer bend and an inner bend extending between the outer platform and the inner platform, respectively, and the airfoil.

12. The assembly of claim 11, further comprising the outer and inner curved portions being circular arc shaped and having an outer radius and/or an inner radius, respectively.

13. The assembly of claim 10, further comprising the fastening plate and the handle, the fastening plate and the handle being integrally formed.

14. The assembly of claim 10, further comprising the outer and inner fastening plates substantially completely or partially covering the outer and inner platforms, respectively.

15. The assembly of claim 7, further comprising:

an outer fastener securing the outer platform to the outer cover or shell,

the outer fastener includes a shank extending generally perpendicularly from an outer fastening plate through an aperture in the outer platform and through an outer aperture in the outer cover or shell, an

A nut threaded onto the threaded end of the shank.

16. The assembly of claim 15, further comprising an outer bend extending between the outer platform and the airfoil, and the outer bend is circular arc shaped and has an outer radius.

17. The assembly of claim 15, further comprising the fastening plate and the handle, the fastening plate and the handle being integrally formed.

18. The assembly of claim 15, further comprising the fastening plate substantially completely or partially covering the outer platform.

19. The assembly of claim 7, further comprising:

an inner fastener securing the inner platform to the inner shroud,

the inner fastener includes a shank extending generally perpendicularly from an inner fastening plate through a platform aperture in the inner platform and through an inner bore in the inner cover, an

A nut threaded onto the threaded end of the shank.

20. The assembly of claim 19, further comprising an inner bend extending between the inner platform and the airfoil, and wherein the inner bend is circular arc shaped and has an inner radius.

21. The assembly of claim 19, further comprising the fastening plate and the handle, the fastening plate and the handle being integrally formed.

22. The assembly of claim 19, further comprising the fastening plate substantially completely or partially covering the inner platform.

Technical Field

The present invention relates generally to turbine components having composite airfoils (e.g., bucket segments), and more particularly to composite bucket segments having integral composite airfoils and platforms.

Background

Turbomachines (e.g., gas turbine engines) may be used for power generation as well as for aircraft and marine propulsion, among other applications, turbomachines include buckets, and it is known to manufacture these buckets from composite layers or laminates. Aircraft gas turbine engines flow air into a fan, then compress some of the air in a compressor, mix the compressed air with fuel and combust the mixture in a combustor to produce hot combustion gases. The gases flow downstream through a High Pressure Turbine (HPT) having one or more stages including one or more HPT turbine nozzles, a shroud, and a plurality of rows of HPT rotor blades. The gases then flow to a Low Pressure Turbine (LPT), which typically includes multiple stages with corresponding LPT turbine nozzles, shrouds, and LPT rotor blades. Air from the fan that does not flow into the compressor may bypass the compressor and be discharged from the fan through the fan outlet guide vanes. Vanes are known which construct layers of composite materials.

U.S. patent No.9,103,214 entitled "ceramic matrix composite vane structure with overwrap for gas turbine engine" discloses a vane structure for a gas turbine engine that includes an airfoil portion having a platform section adjacent a ring. The airfoil portion includes a pressure side and a suction side formed by respective first and second pluralities of CMC layers and respective platform segments. The plurality of CMC single tape layers are bent apart in the triangular region and continue to form respective platform segments. These triangular areas are subject to high interlaminar tensile stresses due to the force differential between the pressure and suction sides. The layers branching in both directions from the airfoil to the platform, along with the main pressure side loads, generate inter-layer tensile and compressive (ILT and ILC) stresses in the fillet through the triangular area commonly referred to as a fillet or triangle. Low ILT (interlayer tensile) materials allow for a negative stress margin.

It is desirable to have a monolithic (singlet) with monolithic airfoils and platforms with as low interlaminar tensile and compressive stresses as possible.

Disclosure of Invention

A composite airfoil monomer includes an airfoil extending from a base of the airfoil to a tip of the airfoil and integrally formed with no more than one outer platform at the tip and/or no more than one inner platform at the base. The airfoil may extend longitudinally or radially from a base to a tip, the outer platform may extend laterally or circumferentially from the tip in a right-hand or clockwise direction, or in a left-hand or counterclockwise direction, and the inner platform may extend laterally or circumferentially from the base in a right-hand or clockwise direction, or in a left-hand or counterclockwise direction.

The cells include parallel composite layers or woven fibers that extend through the airfoil and through the outer platform and/or the inner platform. The outer and/or inner bends may extend between the outer and/or inner platforms, respectively, and the airfoil. The outer and/or inner curves may be circular arcs and have an outer and/or inner radius, respectively.

The assembly of composite aerofoil units may comprise a circular row of composite aerofoil units depending radially inwardly from and mounted to the shroud or casing. The outer and/or inner fasteners may secure the outer and inner platforms to the outer and inner housings, respectively, and may include a shank extending generally perpendicularly from the outer and inner fastening plates through platform apertures in the outer and inner platforms, respectively, and through outer and inner apertures in the outer and inner housings, respectively. The nut may be threaded onto the threaded end of the shank.

The fastening plate and the shank may be integrally formed. The outer and inner fastening plates may substantially completely or partially cover the outer and inner platforms, respectively.

Drawings

The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the concluding portion of the specification. The invention, in accordance with preferred and exemplary embodiments, together with further objects and advantages thereof, is described in the following detailed description taken in conjunction with the accompanying drawings, in which:

FIG. 1 is a longitudinal, partial section and partial schematic view illustrating an exemplary embodiment of an aircraft turbofan gas turbine engine having an exemplary composite airfoil monoblock with no more than one platform at either end of the airfoil.

FIG. 2 is a schematic perspective view illustrating an exemplary airfoil monoblock having no more than one platform at either end of the airfoil.

Fig. 3 is a schematic sectional view showing a single body passing through 3-3 in fig. 2.

Fig. 4 is a schematic sectional view showing the outer platform of the cell passing through 4-4 in fig. 2.

FIG. 5 is a perspective schematic view illustrating an alternative airfoil unitary body having only one outer integral platform at the tip of the airfoil and no inner integral platform at the base of the airfoil.

Fig. 6 is a perspective view of two of the airfoil units shown in fig. 2 mounted on the inner shroud.

FIG. 7 is a cross-sectional schematic view of the airfoil monobloc shown in FIG. 2 in a compressor section of an exemplary gas turbine engine.

Fig. 8 is a perspective view of the outer portion of the airfoil unitary body and the outer support plate shown in fig. 7.

Fig. 9 is a partially exploded perspective view of the inner portion and the inner support plate of the airfoil unit shown in fig. 7.

FIG. 10 is a perspective view of a single stage airfoil in the compressor half shell of the compressor section shown in FIG. 7.

Detailed Description

As shown in FIG. 1, FIG. 1 is an exemplary turbomachine illustrated as an aircraft turbofan gas turbine engine 10 about an engine centerline axis 12. Engine 10 includes, in downstream serial flow communication, a fan section 14, a high pressure compressor 16, a combustor 18, a High Pressure Turbine (HPT)20, and a Low Pressure Turbine (LPT) 22. The HPT or high pressure turbine 20 is connected to the high pressure compressor 16 by a high pressure drive shaft 21. The LPT or low pressure turbine 22 is connected to the fan section 14 by a low pressure drive shaft 23. A splitter 24 surrounding the high pressure compressor 16 directly aft of the fan section 14 splits fan air 26 pressurized by the fan section 14 into a radially inner flow of core airflow 15 through the high pressure compressor 16 and a radially outer flow of bypass airflow 17 through a bypass duct 28 surrounding the high pressure compressor 16, combustor 18, high pressure turbine 20, and low pressure turbine 22. Exhaust gas 30 from the low pressure turbine 22 and the bypass airflow 17 is directed into an exhaust section 32 and then into an exhaust nozzle 34. The fan blade 36 in the fan section 14 may include a composite airfoil unitary body 40, the composite airfoil unitary body 40 being shown in more detail in fig. 2 and 7.

The exemplary embodiment of composite airfoil unitary body 40 shown in FIG. 2 includes an airfoil 42, airfoil 42 being integrally or monolithically formed with no more than one platform 44 at either end of airfoil 42. The airfoil extends from a base 45 to a tip 46, with no more than one outer platform 50 extending circumferentially from the tip 46 in either a clockwise direction C or a counterclockwise direction CC, and/or no more than one inner platform 54 extending circumferentially from the base 45 in either a clockwise direction C or a counterclockwise direction CC, as shown in fig. 9. The composite airfoil cells 40 are made of parallel composite layers 56 or woven fibers that extend through the entire cell 40, through the airfoil 42 and through the outer platform 50 and/or the inner platform 54, as shown in fig. 3 and 4. The composite airfoil single body 40 shown in FIG. 5 has only one outer platform 50 at the tip 46 of the airfoil 42.

The exemplary embodiment of composite airfoil single body 40 as shown in fig. 2 and 3 includes an outer platform 50 and an inner platform 54, with outer platform 50 and inner platform 54 extending circumferentially away from a suction side 68 and a pressure side 70, respectively, of airfoil 42. The outer and inner flexures 73 and 75 of the singlet 40 extend between the outer and inner platforms 50 and 54, respectively, and the airfoil 42. The outer and inner curved portions 73, 75 may be circular arc shaped and include outer and inner radii 72, 74, respectively. The parallel composite layer unit 40 may be manufactured by multi-axis compression molding or by resin transfer molding.

Fig. 2, 4, 6, 7 and 10 illustrate outer fasteners 76 and inner fasteners 78, the outer fasteners 76 and inner fasteners 78 being used to secure the cell 40 in the turbine or engine 10 via the outer platform 50 and inner platform 54. As shown in fig. 1 and 10, circular rows 93 of cells 40 extend radially inward from housing or casing 96 and are mounted to housing or casing 96 by external fasteners 76. The single body 40 extends radially inward to the inner shroud 60 and is mounted to the inner shroud 60 by an inner mount 78. The inner shroud 60 includes a forward flange 100 and an aft flange 102, the forward and aft flanges 100, 102 being sealed by rotating forward and aft seals 104, 106 on a rotor 108 of the turbine or engine 10, as shown in FIG. 7.

Referring to fig. 4, 7 and 9, the outer and inner fasteners 76, 78 include a shank 80 extending generally perpendicularly from outer and inner fastening plates 84, 86 through platform apertures 82 of the outer and inner platforms 50, 54, respectively, and through outer and inner apertures 83, 85 in the outer and inner shrouds, or shells, 96, 60, respectively. Nuts 88 are threaded onto threaded ends 90 of the shank 80 to secure the outer platform 50 and the inner platform 54 to the outer housing or shell 96 and the inner housing 60, respectively. The fastening plate and the shank may be integrally formed. Outer fasteners 76 and inner fasteners 78 may completely or partially cover outer platform 50 and inner platform 54, respectively.

FIG. 6 shows two adjacent singlets 40 mounted together on a common inner shroud 60 to form doublets 79, the doublets 79 being used to build an entire stage of the bucket. Fig. 2-10 illustrate a stator vane assembly 92 that may be found in engine 10. As shown in fig. 2, circular rows 93 of cells 40 rest radially inward from housing or shell 96 and are mounted to housing or shell 96 by external fasteners 76. The single body 40 extends radially inward to the inner shroud 60 and is mounted to the inner shroud 60 by inner fasteners 78. The inner shroud 60 includes a forward flange 100 and an aft flange 102, the forward and aft flanges 100, 102 being sealed by rotating forward and aft seals 104, 106 on a rotor 108 of the turbine or engine 10, as shown in FIG. 7.

While there have been described herein what are considered to be preferred and exemplary embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein, and it is, therefore, desired to be secured in the appended claims all such modifications as fall within the true spirit and scope of the invention. Accordingly, what is desired to be secured by letters patent of the United states is the invention as defined and differentiated in the following claims.