阅读说明：本技术 涡轮机械密封装置和方法 (Turbomachine sealing device and method ) 是由 赖安·克里斯托弗·琼斯 丹尼尔·恩迪科特·奥斯古德 扎迦利·丹尼尔·韦伯斯特 格雷戈里·T·加 于 2019-07-30 设计创作，主要内容包括：一种涡轮机械密封装置,包括具有第一端面的第一涡轮机械部件和远离第一端面延伸的密封件,该密封件通过在部件的壁和密封件之间延伸的接片连接到该壁。(A turbomachinery sealing device includes a first turbomachinery component having a first end face and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.)

1. A turbomachine sealing device comprising a first turbomachine component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

2. The apparatus of claim 1, wherein the wall defines a portion of a first seal groove in communication with the first end face, and a portion of the seal is received in the first seal groove.

3. The apparatus of claim 2, further comprising a second turbomachine component disposed adjacent the first turbomachine component, the second turbomachine component having a second end face and a second seal groove formed in the second end face, wherein a portion of the seal extends into the second seal groove to seal a gap between the first end face and the second end face when the first turbomachine component and the second turbomachine component are disposed adjacent to each other.

4. The device of claim 1, wherein the seal, tab and wall form a unitary structure.

5. The device of claim 1, wherein the seal extends away from the first end face at an oblique angle.

6. The device of claim 1, wherein the tab has a thickness less than a thickness of the seal.

7. The apparatus of claim 1, wherein the seal includes a metering hole formed therethrough.

8. The apparatus of claim 2, wherein the first turbomachine component comprises a second end face opposite the first end face, the second end face comprising a second seal groove.

9. A turbomachine sealing device comprising a plurality of first turbomachine components as recited in claim 8, arranged in a ring, wherein the first end face of each of the first turbomachine components is disposed adjacent the second end face of an adjacent one of the first turbomachine components such that a portion of the seal in each of the first turbomachine components extends into the second seal groove of one of the first turbomachine components, thereby sealing a gap between adjacent ones of the plurality of first turbomachine components.

10. A method of assembling a turbomachine sealing device, comprising the steps of:

providing a first turbomachine component having a seal connected thereto by a tab;

providing a second turbomachine component; and

positioning the first and second turbomachine components adjacent to each other such that the seal spans a gap between the two turbomachine components.

Technical Field

The present invention relates generally to sealing leak paths in engines. More particularly, the present invention relates to seals, such as spline seals, used in leakage paths of turbine hardware or other hardware, where the seals are used to seal leakage between components.

Background

Stationary and rotating turbine engine components, such as turbine stators or nozzles, buckets, bucket shrouds and combustors, are typically constructed as a ring of side-by-side segments. It is known that leakage at the gaps between adjacent sections results in inefficiencies in aircraft engines. Therefore, air leakage between adjacent sections must be minimized to meet engine performance requirements. This is typically achieved using a spline seal, which is a small metal strip that is received in seal grooves formed in two adjacent segments, bridging the gap between the two adjacent segments. Each groove formed in an adjacent segment receives one half of a spline seal.

In conventional seal assemblies, sealing the leak paths requires cumbersome assembly and, because of the assembly of multiple modules, numerous seals must be carefully inserted to seal each leak path, potentially resulting in misplacement and/or improper installation of the seals. For example, in a ring of turbine blades or a ring of stationary turbine nozzles or a ring of turbine shrouds, there may be 30 to 70 joint lines, each of which requires a seal. Assembling all seals is complicated and time consuming.

Disclosure of Invention

At least one of the above problems is addressed by a seal manufactured using casting and/or other manufacturing methods that allow the seal to be connected and/or integrally formed with an adjacent one of the segments and to remain in place during assembly of the adjacent segments, thereby preventing misplacement and/or incorrect installation of the seal.

According to one aspect of the technology described herein, a turbomachinery sealing device includes a first turbomachinery component having a first end surface and a seal extending from the first end surface, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

According to another aspect of the technology described herein, a method of assembling a turbomachine sealing device includes the steps of: providing a first turbomachine component having a seal connected thereto by a tab; providing a second turbomachine component; the first and second turbomachine components are positioned adjacent to each other such that the seal spans a gap between the two turbomachine components.

According to another aspect of the technology described herein, a method of assembling a turbomachine component includes the steps of: providing a plurality of turbomachine segments, each of the plurality of turbomachine segments having a first end face and a second end face opposite the first end face, the first end face including a first seal groove, the second end face including a second seal groove, the first seal groove having a seal disposed therein, the seal connected to a wall of the first seal groove by a tab extending between the wall of the first seal groove and the seal; and providing a plurality of turbomachine segments having first end faces adjacent to second end faces of adjacent turbomachine segments such that a portion of a respective seal extends into the second seal groove.

Drawings

The invention may best be understood by reference to the following description taken in conjunction with the accompanying drawings in which:

FIG. 1 is a perspective view of two nozzle segments assembled together;

FIG. 2 is an exploded perspective view of FIG. 1 showing a spline seal and seal groove for sealing the leakage path of the assembled nozzle segment;

FIG. 3 is a cross-sectional view of FIG. 1 illustrating a prior art method of assembling two nozzle segments;

FIG. 4 is a cross-sectional view illustrating an exemplary method of assembling a plurality of nozzle segments;

FIG. 5 illustrates a seal installed in a seal groove of an adjacent nozzle segment assembled by the method of FIG. 4, wherein the seal is separated from the seal groove after assembly;

FIG. 6 illustrates a seal installed in a seal slot of adjacent nozzle segments after assembly by the method of FIG. 4, wherein the seal remains connected to one of the seal slots;

FIG. 7 illustrates a seal installed in the seal slots of adjacent nozzle segments after assembly by the method of FIG. 4, wherein the seal remains attached to one of the seal slots and contains at least one hole;

FIG. 8 is an exploded schematic view showing an alternative seal embodiment in which a component has a seal extending from opposite faces thereof; and

fig. 9 is an assembled view of the components of fig. 8.

Detailed Description

Referring to the drawings, wherein like reference numbers refer to like elements throughout the several views, FIG. 1 depicts two exemplary turbine nozzle segments 10, 100 secured together to form a portion of a turbine nozzle in a gas turbine engine. Turbine nozzles are but one example of a number of assemblies of turbomachine components within a gas turbine engine or similar turbomachine, where an annular assembly is made up of two or more components with gaps between the components that require sealing. These are referred to herein as "seal assemblies". Such components may be located anywhere in the engine and are not limited to a particular module. Such assemblies are typically, but not always, made up of a single ring of arcuate segments. Non-limiting examples of components or segments that make up the seal assembly include the inner or outer band of a stationary airfoil blade, the end of a platform or shroud segment of a turbomachine blade.

The first nozzle segment 10 includes an inner band 12, the inner band 12 being connected to an outer band 14 by airfoils 16. The outer band 14 has an inner side surface 18 and an outer side surface 20. The end surface 22 of the outer band 14 is located between the inboard surface 18 and the outboard surface 20. Similarly, the second nozzle segment 100 includes an inner band 112, and the inner band 112 is coupled to an outer band 114 via airfoils 116. The outer band 114 has an inner side surface 118 and an outer side surface 120. The end surface 122 of the outer band 114 is located between the inboard surface 118 and the outboard surface 120.

Referring now to fig. 2-6, each end face 22 and 122 includes a seal groove 30 and 130, respectively, with the seal grooves 30 and 130 extending inwardly from the end faces 22, 122 and configured to receive the spline seal 40 therein. As shown in fig. 3-6, when the turbine nozzle segments 10, 100 are assembled in a ring or annular array, the end faces 22, 122 are in close proximity to one another in facing relationship with a small gap "G" defined therebetween. The spline seal 40 is received in the seal groove 30, 130 of the adjacent segment 10, 100 and spans the gap G. Typically, the spline seal 40 is a thin plate-like member of metal stock having opposed outer and inner surfaces 42, 44. The function of the spline seal 40 is to prevent air from leaking through the gap G.

The seal slot 30 is defined by a bottom wall 32, an inner sidewall 34 and an outer sidewall 36, and is closed by two end walls (not shown). The inner and outer side walls 34, 36 extend from the bottom wall 32 to an edge 38 at the end face 22.

Likewise, the seal slot 130 is defined by a bottom wall 132, an inner sidewall 134, and an outer sidewall 136, and is closed by two end walls (not shown). Inner and outer side walls 134, 136 extend from the bottom wall 132 to a rim 138 at the end face 122.

The seal grooves 30, 130 have a base depth D defined by their shallowest portions, which represents the desired setting depth of the respective spline seal 40. For example, the setting depth D may be about half the overall width W of the spline seal 40. When assembled, the spline seal 40 fills substantially the entire volume of the seal grooves 30, 130.

As shown in fig. 3, the prior art assembly method requires insertion of the seal 40 into the slots 30, 130 and then securing the segments 10, 100 together. The purpose of seal 40 is to prevent air from leaking from the area labeled "P1" to the area labeled "P2". In effect, the pressure differential between P1 and P2 causes the inner surface 44 of the seal 40 to abut the inner side wall 34, 134 of each groove 30, 130, thereby blocking flow. Typically, a clearance of about 0.254mm (0.010 inches) is provided between the outer surface 42 and the outer side walls 36, 136, and a clearance of about 0.254mm (0.010 inches) is provided between the inner surface 44 of the seal 40 and the inner side walls 34, 134. There is some inconsistency in how the seal 40 operates because it can move around in the groove 30, 130 until the pressure differential causes the seal 40 to abut the inner sidewall 34, 134.

Note that the region generally labeled "P1" is part of the secondary flowpath, i.e., it is located on the "cold side" of the hardware. The region labeled "P2" is part of the primary flow path, i.e., the "hot side" of the hardware where the hot combustion gases flow. The seal 40 prevents the hot combustion gases from flowing into the secondary flowpath. Typically, the pressure differential is maintained to provide a backflow margin, i.e., to ensure that hot flowpath gases are not drawn into the secondary flowpath even if the seal 40 is not completed. Thus, in some cases it is desirable to minimize purge flow, and the ability to meter flow using a seal would be helpful. As mentioned above, such assembly is complicated and cumbersome due to the number of assemblies of seals and segments and due to misalignment and/or incorrect mounting of the seals.

Referring to fig. 4-6, the present concept uses manufacturing techniques such as investment casting, additive manufacturing, and Electrical Discharge Machining (EDM) to form the grooves 30, 130 and the seal 40. This results in the seal 40 being integrally formed (i.e., of unitary or one-piece construction) or secured to one of the slots 30, 130 and allows adjacent segments 10, 100 to be secured together without the need to manually insert the seal 40 into the slot 30, 130. This fabrication also allows for tighter control of the tolerances between the grooves 30, 130 and the seal 40 to provide better sealing and drive the gas flow away from potential leak paths. FIG. 4 shows the turbine nozzle segments 10, 100 assembled with the seal 40, the seal 40 being connected to adjacent turbine nozzle segments 10, 100. This approach does not require complex sealing assemblies.

As shown, the seal member 40 is connected to the bottom wall 32 of the channel 30 and the bottom wall 132 of the channel 130 by tabs or channels 150 between the seal member 40 and the bottom walls 32, 132. As used herein, the term "coupled" when describing two elements refers to a joint or interconnection between the elements, and not merely a contact (e.g., friction, pressure) between the two. As used herein, the term "tab" refers to a relatively elongated mechanical interconnection element that need not have any particular cross-sectional shape. Synonyms for the term "tab" include, for example: sprue, ligament, connector or beam. As shown, the thickness "T" of the tab or channel 150_t"less than the thickness of the seal 40" T_s". It should be appreciated that instead of the seal 40 being attached to the bottom wall 32, 132, the seal 40 may be attached to one or more of the inner sidewall 34, outer sidewall 36, inner sidewall 134 or outer sidewall 136 by one or more tabs, and adjacent turbine nozzle segments 10, 100 may be assembled so long as the seal 40 is attached to at least one wall of the slot 30, 130.

The tabs or channels 150 may function in different ways. For example, the tabs or tunnels 150 may be very thin and/or otherwise fragile. The purpose of this is to secure the seal 40 in place to make assembly easier. Thus, as an example, two turbine nozzle segments 10, 100 may be assembled with one of the turbine nozzle segments 10, 100 having the integrated seal 40. Then, once they are assembled, the seal can be broken or shaken off using a tool to release it (which can be done by pin striking or cutting/grinding tools), as shown in fig. 5. This method can be used for many seal types and even dampers on turbine blades.

In another example, as shown in fig. 6, the tabs or tunnels 150 may be slightly thicker to hold the seal 40 in place, but allow it to move around to find the sealing position in the grooves 30, 130. In this example, the tabs or channels 150 are connected to the bottom walls 32, 132 and will not break and will provide a spring force, like a spring element, to resist the differential pressure force between the opposing outer and inner surfaces 42, 44 of the seal 40, thereby providing a variable restriction that will allow for the metering of leakage flow. Further, as shown in FIG. 7, the seal 40 may include a hole or groove 46 formed through its thickness to allow metering of the purge flow when the seal 40 is in the fully sealed position, e.g., the seal 40 prevents gas flow leakage.

A variety of physical configurations of the above-described seal structures are possible. For example, fig. 8 and 9 illustrate an assembly 200 that includes a first component 202, a second component 204, and a third component 206, respectively. First member 202 and third member 206 each include an end face 222, end face 222 having a seal groove 230 formed therein. In the example shown, each seal groove 230 extends from a respective end face 222 at an oblique angle. In the assembled orientation, seal grooves 230 are angled with respect to each other.

The second component 204 has end faces 224 on opposite sides thereof, each end face 224 having a seal 240 connected thereto by tabs 250. The thickness of the tab 250 may be less than the thickness of the seal 240. In this example, the seal 240 extends away from the end face 224 at an oblique angle, generally presenting a V-shape in a front or rear view.

The components 202, 204 and 206 may be assembled by moving them in the direction of the arrows, i.e. in combination with axial and lateral movements. Fig. 9 shows the components 202, 204 and 206 in an assembled state, in which each seal 240 is received in one of the seal grooves 230.

The embodiments of fig. 8 and 9 illustrate the following concepts: the seal connected by the tabs as described above may extend from the face of one component and be fully received in the groove of the meeting component; or, in other words, not every component need include a seal groove. This embodiment further illustrates the concept of: a given component may have two or more seals extending from opposite sides thereof that are received in the grooves of two adjacent components. Providing a seal that extends at an oblique angle allows for physical assembly of generally angled or arcuate structures from these components.

The current technology provides the benefits of eliminating the assembly steps, simplifying the overall assembly process and allowing for tightly controlled manufacturing tolerances to introduce better sealing effectiveness and drive airflow away from potential leakage paths; thus, performance is improved.

The foregoing has described a turbomachine apparatus and method. All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and/or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations where some of such features and/or steps are mutually exclusive.

Each feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.

The invention is not restricted to the details of the foregoing embodiments. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification (including any accompanying claims, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.

Further aspects of the invention are provided by the subject matter of the following clauses:

1. a turbomachinery sealing device comprising a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

2. The apparatus of any preceding claim, wherein the wall defines a portion of a first seal groove in communication with the first end face, and a portion of the seal is received in the first seal groove.

3. The apparatus of any preceding claim, further comprising a second turbomachine component disposed adjacent the first turbomachine component, the second turbomachine component having a second end face and a second seal groove formed in the second end face, wherein a portion of the seal extends into the second seal groove to seal a gap between the first end face and the second end face when the first turbomachine component and the second turbomachine component are disposed adjacent to each other.

4. The device according to any preceding claim, wherein the seal, tab and wall form a unitary structure.

5. The apparatus of any preceding claim, wherein the seal extends away from the first end face at an oblique angle.

6. The device according to any preceding claim, wherein the tab has a thickness less than a thickness of the seal.

7. The apparatus according to any preceding claim, wherein the seal comprises a metering hole formed therethrough.

8. The apparatus of any preceding claim, wherein the first turbomachine component comprises a second end face opposite the first end face, the second end face comprising a second seal groove.

9. A turbomachinery sealing device comprising a plurality of first turbomachinery components of any of the preceding items arranged in a ring, wherein said first end face of each said first turbomachinery component is disposed adjacent to said second end face of an adjacent one of said first turbomachinery components such that a portion of said seal in each said first turbomachinery component extends into said second seal groove of one of said first turbomachinery components, thereby sealing a gap between adjacent ones of said first turbomachinery components.

10. A method of assembling a turbomachine sealing device, comprising the steps of: providing a first turbomachine component having a seal connected thereto by a tab; providing a second turbomachine component; and positioning the first and second turbomachine components adjacent to each other such that the seal spans a gap between the two turbomachine components.

11. The method according to any preceding item, wherein the seal, tab and first turbomachine component form a unitary structure.

12. The method according to any preceding item, further comprising the step of breaking the tab after positioning the first and second turbomachine components.

13. The method of any preceding item, the first segment comprising a first end face having a first seal groove formed therein.

14. The method of any preceding claim, wherein the seal is disposed within the first seal groove and is connected to a wall of the first seal groove by the tab.

15. The method of any preceding item, wherein the second segment includes a second end face having a second seal groove formed therein.

16. The method of any preceding item, further comprising the step of positioning the first end face adjacent the second end face to allow a portion of the seal to be positioned in the second seal groove.

17. The method according to any preceding claim, wherein the seal comprises a metering hole.

18. A method of assembling a turbomachine component comprising the steps of: providing a plurality of turbomachine segments, each of the plurality of turbomachine segments having a first end face and a second end face opposite the first end face, the first end face including a first seal groove, the second end face including a second seal groove, the first seal groove having a seal disposed therein, the seal connected to a wall of the first seal groove by a tab extending between the wall and the seal; and disposing the plurality of turbomachine segments such that a first end face of one turbomachine segment is adjacent to a second end face of an adjacent turbomachine segment such that a portion of a respective seal extends into the second seal groove.

19. The method according to any preceding item, further comprising the step of breaking the tabs after positioning the plurality of turbomachine segments together.

20. The method according to any preceding item, wherein the seal, tab and turbomachine section form a unitary structure.