Turbine bucket lockwire anti-rotation device for gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/30
F01D-005/32
F01D-025/04
F01D-005/12
출원번호
US-0067511
(2016-03-11)
등록번호
US-10145249
(2018-12-04)
발명자
/ 주소
Poth, Leissner F.
Danyew, Clayton
Lovinger, David Jesse Warren
Hingorani, Sanjay Surat
출원인 / 주소
Mechanical Dynamics & Analysis LLC
대리인 / 주소
Burris Law, PLLC
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A gas turbine engine system comprises a rotor wheel, a plurality of blades, a lockwire and a locking key. The rotor wheel comprises a plurality of axial grooves extending through a periphery of the rotor wheel, and a plurality of posts formed between adjacent slots, each post having a circumferentia
A gas turbine engine system comprises a rotor wheel, a plurality of blades, a lockwire and a locking key. The rotor wheel comprises a plurality of axial grooves extending through a periphery of the rotor wheel, and a plurality of posts formed between adjacent slots, each post having a circumferential slot. The blades are mounted in the axial grooves of the rotor wheel, each blade having a circumferential slot circumferentially aligned with the circumferential slots of the posts. The lockwire extends across the plurality of axial grooves of the rotor wheel within each of the circumferential slots of the posts and the blades from a first end to a second end to inhibit axial displacement of the blades within the grooves. The locking key is disposed between the first and second ends of the lockwire and provides support to at least one of the ends of the lockwire to prevent radially inward displacement.
대표청구항▼
1. A gas turbine engine system comprising: a rotor wheel comprising: a plurality of axial grooves extending through a periphery of the rotor wheel; anda plurality of posts formed between adjacent grooves, each post of the plurality of posts having a circumferential slot;a plurality of blades mounted
1. A gas turbine engine system comprising: a rotor wheel comprising: a plurality of axial grooves extending through a periphery of the rotor wheel; anda plurality of posts formed between adjacent grooves, each post of the plurality of posts having a circumferential slot;a plurality of blades mounted in the plurality of axial grooves of the rotor wheel, each blade of the plurality of blades having a circumferential slot circumferentially aligned with the circumferential sots of the plurality of posts;a lockwire extending across the plurality of axial grooves of the rotor wheel within each of the circumferential slots of the posts of the plurality of posts and the blades of the plurality of blades from a first end to a second end to inhibit axial displacement of the plurality of blades within the plurality of axial grooves; anda locking key disposed between the first and second ends of the lockwire to provide support to at least one of the first and second ends of the lockwire to prevent the at least one of the first and second ends from being displaced radially inward without inhibiting radial outward displacement, the locking key comprising: a central portion positioned between the ends of the lockwire and for linking the locking key to the rotor wheel; andat least one arm extending laterally from the central portion for positioning the at least one of the first and second ends of the lockwire against an underside of at least one of the circumferential slots of the plurality of posts and restricting radially inward displacement of the at least one of the first and second ends of the lockwire. 2. The gas turbine engine system of claim 1, wherein the locking key includes a pair of arms including the at least one arm extending in opposite lateral directions from the central portion to support each of the first and second ends of the lockwire, respectively. 3. The gas turbine engine system of claim 2, wherein each arm has a saddle for receiving an end of the lockwire, the saddles being open in a radially outward direction. 4. The gas turbine engine system of claim 2, wherein each arm has a height near the central portion that tapers toward a lateral end of each arm. 5. The gas turbine engine system of claim 2, wherein the central portion comprises a tab located between the first and second ends of the lockwire, the tab projecting radially beyond outer surfaces of the pair of arms to provide a circumferential stop. 6. The gas turbine engine system of claim 5, wherein the tab has a width [approximately] equal to a distance between the first and second ends of the lockwire. 7. The gas turbine engine system of claim 5, wherein a distance between the first and second ends of the lockwire grows from a first gap length to a second gap length during operation of the gas turbine engine system, and wherein each of the arms of the pair of arms is longer than a difference between the second gap length and a width of the tab. 8. The gas turbine engine system of claim 1, further comprising: a fastener extending through one of the circumferential slots in one of the plurality of posts and extending through the central portion to link the locking key to the rotor wheel. 9. The gas turbine engine system of claim 8, wherein the central portion includes a slot for receiving the fastener. 10. The gas turbine engine system of claim 1, further comprising a counter-weight located on the rotor wheel one-hundred-eighty degrees from the locking key. 11. A retention system for turbine blades in a gas turbine engine having a lockwire extending in a circular pathway from a first end to a second end such that a gap is present between the first and second ends, the retention system comprising: a locking key comprising: a central portion for placement between the first and second ends of the lockwire to prevent circumferential rotation of the lockwire; andat least one arm extending laterally from the central portion for providing radial support to the first and second ends of the lockwire,wherein the locking key prevents the first and second ends from being displaced radially inward without inhibiting radial outward displacement. 12. The retention system of claim 11, wherein each arm having a saddle for receiving an end of the lockwire. 13. The retention system of claim 11, wherein each arm has a height near the central portion that tapers toward a lateral end of each arm. 14. The retention system of claim 11, further comprising a pin for extending through the central portion of the locking key. 15. A method of retaining a lockwire in a gas turbine engine system, the method comprising: inserting the lockwire into a plurality of circumferential slots formed in a plurality of posts of a turbine wheel and a plurality of circumferential slots formed in a plurality of blade roots inserted between the plurality of posts; andinserting a locking key into a gap between ends of the lockwire, the locking key comprising at least one arm extending therefrom, the at least one arm positioned radially inward of the ends of the lockwire, wherein the locking key is inserted by sliding the locking, key radially upward into one of the plurality of circumferential slots to engage the at least one arm with the lockwire. 16. The method of claim 15, further comprising: measuring the gap between the ends of the lockwire before inserting the locking key; and removing material from at least one end of the lockwire until the gap has a length equal to a width of a tab on the locking key. 17. The method of claim 15, wherein the lockwire is positioned such that an end of the lockwire is located adjacent a fastener bore in a post of the plurality of posts of the turbine wheel. 18. The method of claim 17, further comprising inserting a fastener through the locking key and into the fastener bore to secure the locking key to the turbine wheel. 19. The method of claim 15, further comprising: expanding the lockwire such that a gap distance between ends of the lockwire increases over an arc; andsliding at least one end of the lockwire along one of the arms along an entire length of the arc of the gap distance.
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이 특허에 인용된 특허 (11)
Libertini Zoltan L. (Stamford CT) Ivanko Theodore (Fairfield CT), Boltless blade retainer for a turbine wheel.
Boston,Erick Jacques; Bromann,Alain Marc Lucien; Debeneix,Pierre; Eichstadt,Frederic Paul, Device for blocking a ring for axially retaining a blade, associated rotor disk and retaining ring, and rotor and aircraft engine comprising them.
Bouru, Michel A.; Charbonnel, Jean-Louis; Prato, Jean-Claude, Sealing and retaining device for a rotor notched with pin settings receiving blade roots.
Eastman, John Alan; Arness, Brian Peter; Honkomp, Mark Steven; Wassynger, Stephen Paul; Byam, Steve P.; Reinker, Michael, Turbine bucket lockwire rotation prevention.
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