Pin to reduce relative rotational movement of disk and spacer of turbine engine
An axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation. Each of a disk and a spacer of the disk and spacer pairs has a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer. The head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer.
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The present disclosure relates generally to turbine engines and, more particularly, to a pin for reducing relative rotational movement of a disk and a spacer of an axial compressor of the turbine engine.
BACKGROUNDSome axial compressors of turbine engines use spacers to provide an inner flowpath for working fluid. The spacers are typically thin rings, installed onto each of a plurality of disks of the axial compressor. An interference engagement or, more particularly, a thermal interference engagement and a small cylindrical anti-rotation pin are used to couple each spacer to a corresponding disk. The disk and spacer pairs are oriented along a common rotational axis of the axial compressor. During a hot shutdown of the turbine engine, the spacers typically cool and shrink at a higher rate than the corresponding disks, thereby relieving the thermal interference engagement. The rotational inertia of the spacers often breaks the pins, allowing the spacers to rotationally shift relative to the corresponding disks from the factory set positions. To reset the imbalance, the turbine engine may require removal from service and disassembly.
U.S. Pat. No. 8,840,375 to Virkler discloses a lock assembly for a gas turbine engine. The lock assembly includes a lock body with an undercut slot that receives a retaining wire of a polygon shape. A rotor disk has a circumferentially intermittent slot structure extending radially outward relative to an axis of rotation. A component defined about the axis of rotation has multiple radial tabs extending radially inward relative to the axis of rotation. The radial tabs are engageable with the intermittent slot structure. A lock assembly, which includes the retaining wire, is engaged with at least one opening formed by the intermittent slot structure to provide an anti-rotation interface for the component.
As should be appreciated, there is a continuing need to improve efficiency and reliability of turbine engines and components of turbine engines.
SUMMARY OF THE INVENTIONIn one aspect, an axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation. Each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs have a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer. The head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer.
In another aspect, a method of operating a turbine engine includes steps of rotating a disk and spacer pair of a plurality of disk and spacer pairs about a common axis of rotation, and engaging a contacting face of a disk of the disk and spacer pair with a contacting face of a spacer of the disk and spacer pair during rotation. The method also includes a step of restricting relative rotation of the disk and the spacer using a pin having a stem received within a recessed area of the disk and a head received within a recessed area of the spacer. The restricting step includes contacting at least two flats of the head of the pin with complementary surfaces of the recessed area of the spacer.
In yet another aspect, a turbine engine includes an axial compressor. The axial compressor includes a plurality of disk and spacer pairs oriented along a common axis of rotation, with each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a hexagonally shaped head received within the recessed area of the spacer.
A portion of an exemplary turbine engine 10 is shown generally in
Each of a disk 16 and a spacer 18 of the disk and spacer pairs 14 may have a respective contacting face 20, 22 defining an engagement between the disk 16 and the spacer 18. That is, at least some portion of the contacting face 20 of the disk 16 and at least some portion of the contacting face 22 of the spacer 18 may interface or connect to define the engagement. As used herein, the contacting faces 20, 22 of the disk 16 and the spacer 18 may include surfaces of the respective components that face one another.
The disk 16 may have a generally cylindrical body, which may or may not be hollow, including or supporting a plurality of static blades. The spacer 18 may have a thin ring-shaped body for providing space, along the common axis of rotation A1, between the disks 16 and, thus, providing an inner flowpath for working fluid. Each spacer 18 of the disk and spacer pairs 14 may be the same material as the corresponding disk 16, which may, for example, include stainless steel. Although a specific embodiment is described, the present disclosure may be applicable to disks and spacers having various shapes, size, materials, and configurations.
The contacting face 20, 22 of each of the disk 16 and the spacer 18 may include a respective recessed area 24, 26. The recessed areas 24, 26, which may be recessed relative to the respective contacting face 20, 22, may be aligned such that a pin 28 may be positioned as shown. In particular, the recessed areas 24, 26 may be aligned along an axis parallel to the common axis of rotation A1. The pin 28 may generally include a stem 30 and a head 32 and, as will be discussed below, the stem 30 may be received at least partly within the recessed area 24 of the disk 16 and the head 32 may be received at least partly within the recessed area 26 of the spacer 18. During operation of the turbine engine 10, a thermal interference engagement between the disk 16 and the spacer 18 may secure the engagement of the disk 16, spacer 18, and pin 28.
The exemplary pin 28, including the stem 30 and the head 32, is shown generally in
As stated above, but referring now to
The head 32 of the pin 28, according to the present disclosure, may include at least two flats 40 corresponding to complementary surfaces of the recessed area 26 of the spacer 18. That is, the recessed area 26 may include planar surfaces having similar angles as corresponding surfaces of the head 32 of the pin 28. Thus, the recessed area 26 may be shaped, sized, and/or configured such that at least one of the flats 40 contacts or engages a corresponding surface of the recessed area 26 during operation and/or shutdown of the turbine engine 10.
As shown in
The spacer 18 is shown in
As stated above, the head 32 of the pin 28 may include a plurality of flats 40. As such, the recessed area 26 of the spacer 18 may have a shape corresponding to the shape of the head 32 of the pin 28. During operation of the turbine engine 10 or during a shutdown, such as a hot shutdown, the spacer 18 may cool more quickly than the corresponding disk 16, thus reducing the predetermined clearance 50 and causing one or more of the flats 40 to engage one or more corresponding surface of the recessed area 26.
INDUSTRIAL APPLICABILITYThe present disclosure relates generally to turbine engines and, more particularly, to an axial compressor of a turbine engine. Further, the present disclosure relates to an axial compressor having a plurality of disk and spacer pairs. Yet further, the present disclosure is applicable to a pin for reducing relative rotational movement of a disk and a spacer of the disk and spacer pairs.
Referring generally to
Referring specifically to
During operation of the turbine engine 10, a thermal interference engagement between the disk 16 and the spacer 18 of the disk and spacer pair 14 may form. That is, the disk 16, spacer 18, and pin 28 may be configured to rotate together using a frictional fit or engagement. During a hot shutdown, or other similar condition, of the turbine engine 10, a predetermined clearance 50 between a top surface 52 of the head 32 of the pin 28, and an inner surface 54 of the recessed area 26 of the spacer 18 may be reduced.
During the operation and/or shutdown, relative rotation of the disk 16 and the spacer 18 may be reduced or restricted using the pin 28, which has the stem 30 received within the recessed area 24 of the disk 16, and the head 32 received within the recessed area 26 of the spacer 18, at box 66. The restricting step includes contacting at least two flats 40 of the head 32 of the pin 28 with complementary surfaces of the recessed area 26 of the spacer 18, at box 68. According to some embodiments, the restricting step may include engaging four pins 28 with four recessed areas 24, 26 spaced about each of the disk 16 and the spacer 18.
Some conventional axial compressors utilize small cylindrical pins having an interference fit with one or both of a disk and spacer. During a hot shutdown of the turbine engine, the spacer may cool and shrink at a higher rate than the corresponding disk. This may relieve the designed interference fit and cause the spacer to become loose on the disk. The small cylindrical pin is often insufficient to restrain the spacer in the circumferential direction. The force exerted on the pin by the rotational inertia of the spacer may cause the pin to break, thereby freeing the spacer to rotate relative to the disk from the factory setting.
The pin of the present disclosure, as described herein, reduces clocking and provides a more durable and robust engagement of the disk and spacer in the context of an axial compressor, or other similar context. In particular, for example, and during a hot shutdown, of the turbine engine, the spacer may cool more quickly than the corresponding disk, thus reducing the predetermined clearance and causing one or more of the flats to engage one or more corresponding surface of the recessed area.
It should be understood that the above description is intended for illustrative purposes only, and is not intended to limit the scope of the present disclosure in any way. Thus, those skilled in the art will appreciate that other aspects of the disclosure can be obtained from a study of the drawings, the disclosure and the appended claims.
Claims
1. An axial compressor of a turbine engine, including:
- a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer;
- the contacting face of each of the disk and the spacer including a recessed area; and
- a pin having a stem received within the recessed area of the disk and a head received within the recessed area of the spacer;
- the head of the pin including at least two flats corresponding to complementary surfaces of the recessed area of the spacer.
2. The axial compressor of claim 1, wherein the disk and the spacer have a thermal interference engagement.
3. The axial compressor of claim 1, wherein the head of the pin has a hexagonal shape.
4. The axial compressor of claim 3, wherein the recessed area of the spacer has a shape corresponding to the hexagonal shape of the head of the pin.
5. The axial compressor of claim 3, wherein the stem of the pin has a cylindrical shape.
6. The axial compressor of claim 5, wherein the recessed area of the disk has a shape corresponding to the cylindrical shape of the stem of the pin.
7. The axial compressor of claim 3, wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin.
8. The axial compressor of claim 1, further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas.
9. The axial compressor of claim 1, further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer.
10. A method of operating a turbine engine, including steps of:
- rotating a disk and spacer pair of a plurality of disk and spacer pairs about a common axis of rotation;
- engaging a contacting face of a disk of the disk and spacer pairs with a contacting face of a spacer of the disk and spacer pairs during rotation; and
- restricting relative rotation of the disk and the spacer using a pin having a stem received within a recessed area of the disk and a head received within a recessed area of the spacer;
- wherein the restricting step includes contacting at least two flats of the head of the pin with complementary surfaces of the recessed area of the spacer.
11. The method of claim 10, further including forming a thermal interference engagement of the disk and the spacer during operation of the turbine engine.
12. The method of claim 11, further including performing a hot shutdown of the turbine engine, and reducing a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer.
13. The method of claim 10, further including engaging a hexagonally shaped head of the pin with the complementary surfaces of the recessed area of the spacer.
14. The method of claim 10, wherein the restricting step includes engaging four pins with four recessed areas spaced about each of the disk and the spacer.
15. A turbine engine, including:
- an axial compressor, including: a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer, the contacting face of each of the disk and the spacer including a recessed area; and a pin having a stem received within the recessed area of the disk and a hexagonally shaped head received within the recessed area of the spacer.
16. The turbine engine of claim 15, wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin.
17. The turbine engine of claim 15, wherein the stem of the pin has a cylindrical shape.
18. The turbine engine of claim 15, wherein the disk and the spacer have a thermal interference engagement.
19. The turbine engine of claim 15, further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer.
20. The turbine engine of claim 15, further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas.
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Type: Grant
Filed: May 8, 2017
Date of Patent: Aug 20, 2019
Patent Publication Number: 20180320708
Assignee: Solar Turbines Incorporated (San Diego, CA)
Inventor: Kenneth Gregory Thomas (San Diego, CA)
Primary Examiner: John Kwon
Application Number: 15/588,871
International Classification: B63H 1/20 (20060101); F04D 29/64 (20060101); F04D 19/02 (20060101); F04D 29/32 (20060101); F01D 5/06 (20060101); F04D 29/34 (20060101);