Retractable exhaust liner segment for gas turbine engines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/30
F02K-001/82
F02K-001/80
출원번호
US-0808573
(2015-07-24)
등록번호
US-10184358
(2019-01-22)
발명자
/ 주소
Petty, Dale William
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A retractable exhaust liner segment according to an example of the present disclosure includes, among other things, at least one liner segment extending between a forward end and an aft end. The forward end of the at least one liner segment is configured to overlap an aft end of an engine structure
A retractable exhaust liner segment according to an example of the present disclosure includes, among other things, at least one liner segment extending between a forward end and an aft end. The forward end of the at least one liner segment is configured to overlap an aft end of an engine structure and the aft end of the at least one liner segment is configured to overlap a forward end of an exhaust liner when in an assembled position. The at least one liner is configured such that a gap exists between the at least one liner segment and one of the engine structure and the exhaust liner when the at least one liner segment is moved along an axis in a first direction to a disassembled position. The gap closes as the at least one liner segment is moved along the axis in a second, different direction to the assembled position.
대표청구항▼
1. A retractable exhaust liner segment comprising: at least one liner segment extending between a forward end and an aft end;wherein said forward end of said at least one liner segment is configured to overlap an aft end of an engine structure and said aft end of said at least one liner segment is c
1. A retractable exhaust liner segment comprising: at least one liner segment extending between a forward end and an aft end;wherein said forward end of said at least one liner segment is configured to overlap an aft end of an engine structure and said aft end of said at least one liner segment is configured to overlap and contact a forward end of an exhaust liner when in an assembled position, the aft end of the engine structure axially aft of a turbine section with respect to a central longitudinal axis, and the exhaust liner axially aft of the engine structure with respect to a central longitudinal axis; andwherein said at least one liner segment is configured such that an axial gap exists along said central longitudinal axis between said at least one liner segment and one of the engine structure and the exhaust liner when said at least one liner segment is moved along said central longitudinal axis in a first direction to a disassembled position, and the axial gap closes as said at least one liner segment is moved along the axis in a second, different direction to the assembled position. 2. The retractable exhaust liner segment as recited in claim 1, wherein said at least one liner segment includes a first retractable exhaust liner segment and a second retractable exhaust liner segment arranged circumferentially about said central longitudinal axis. 3. The retractable exhaust liner segment as recited in claim 1, wherein said at least one liner segment includes a locating feature configured to axially index said at least one liner segment with respect to at least one of the engine structure and the exhaust liner when in the assembled position. 4. The retractable exhaust liner segment as recited in claim 3, wherein said locating feature defines a step surface configured to abut surfaces of at least one of the engine structure and the exhaust liner. 5. The system as recited in claim 1, wherein said engine structure is an engine tail cone configured to direct engine core flow from said turbine section to said exhaust liner. 6. A retractable exhaust liner segment comprising: at least one liner segment extending between a forward end and an aft end;wherein said forward end of said at least one liner segment is configured to overlap an aft end of an engine structure and said aft end of said at least one liner segment is configured to overlap a forward end of an exhaust liner when in an assembled position;wherein said at least one liner segment is configured such that a gap exists between said at least one liner segment and one of the engine structure and the exhaust liner when said at least one liner segment is moved along an axis in a first direction to a disassembled position, and the gap closes as said at least one liner segment is moved along the axis in a second, different direction to the assembled position;wherein the aft end of the engine structure is axially aft of a turbine section with respect to the axis, and the exhaust liner is axially aft of the engine structure with respect to the axis;wherein said at least one liner segment includes a first retractable exhaust liner segment and a second retractable exhaust liner segment arranged circumferentially about said axis; anda fastener assembly configured to mount a first flange of said first retractable exhaust liner segment to a second flange of said second retractable exhaust liner segment, wherein said fastener assembly includes a T-bolt. 7. The retractable exhaust liner segment as recited in claim 6, further comprising a retainer to retain said T-bolt within said first flange. 8. The retractable exhaust liner segment as recited in claim 7, wherein said second flange includes a slot configured to receive said T-bolt pivotable through said slot. 9. A propulsion system comprising: a gas turbine engine including a turbine section along a central longitudinal axis;an exhaust liner along the central longitudinal axis;a retractable exhaust liner segment configured to span between a portion of said gas turbine engine and said exhaust liner, said portion axially aft of said turbine section with respect to said central longitudinal axis, and said exhaust liner axially aft of said portion with respect to said central longitudinal axis; andwherein said retractable exhaust liner segment is configured such that an axial gap exists along said central longitudinal axis between said retractable exhaust liner segment and one of said portion of said pas turbine engine and said exhaust liner when said retractable exhaust liner segment is moved along the central longitudinal axis in one direction to a disassembled position, and the axial gap closes when said retractable exhaust liner segment is moved along the central longitudinal axis in another direction to an assembled position. 10. The system as recited in claim 9, wherein a forward end of said retractable exhaust liner segment is configured to overlap an aft end of said gas turbine engine and an aft end of said retractable exhaust liner segment is configured to overlap and contact a forward end of said exhaust liner when said retractable exhaust liner segment is located in the assembled position. 11. The system as recited in claim 10, wherein said gas turbine engine includes a fan section, a compressor section and a combustor section, and said fan section is configured to deliver airflow to a core flow path and to a secondary flow path, and said turbine section defines said core flow path. 12. The system as recited in claim 9, wherein said retractable exhaust liner segment includes a first segment and a second segment arranged circumferentially about said central longitudinal axis. 13. The retractable exhaust liner segment as recited in claim 9, wherein said retractable exhaust liner segment and said exhaust liner are mounted within an outer exhaust duct when in the assembled position, said outer exhaust duct mountable to said gas turbine engine through an exhaust duct segment. 14. The system as recited in claim 13, wherein said retractable exhaust liner segment is configured to oppose relative movement between said portion of said gas turbine engine and said exhaust liner when said retractable exhaust liner segment is located in the assembled position. 15. The system as recited in claim 14, wherein said portion of said gas turbine engine is an engine tail cone configured to direct engine core flow to said exhaust liner. 16. The system as recited in claim 15, wherein said exhaust liner and said gas turbine engine are selectively received in an airframe configured to oppose axial movement of said exhaust liner and said gas turbine engine along the central longitudinal axis in a direction away from said retractable exhaust liner segment. 17. The system as recited in claim 14, wherein said gas turbine engine includes a compressor section and a combustor section. 18. The retractable exhaust liner segment as recited in claim 13, wherein said retractable exhaust liner segment include a step surface configured to axially index said retractable exhaust liner segment with respect to at least one of said portion of said gas turbine engine and said exhaust liner when in the assembled position. 19. A method of maintaining a gas turbine engine comprising: telescoping an exhaust liner segment along a central longitudinal axis over one of a portion of a gas turbine engine and a portion of an exhaust liner such that said exhaust liner segment defines an axial clearance gap along the central longitudinal axis between other one of said gas turbine engine and said exhaust liner, said portion of said gas turbine engine axially aft of a turbine section with respect to said central longitudinal axis, and said exhaust liner axially aft of said portion with respect to said central longitudinal axis; andmoving one of said portion of said gas turbine engine and said portion of said exhaust liner transverse to the central longitudinal axis a distance through said axial clearance gap. 20. The method as recited in claim 19, comprising translating a forward end of said exhaust liner segment along the central longitudinal axis such that said forward end of said exhaust liner segment overlaps said portion of said gas turbine engine. 21. The method as recited in claim 19, comprising translating an aft end of said exhaust liner segment along the central longitudinal axis such that said aft end of said exhaust liner segment overlaps and contacts a forward end of said exhaust liner. 22. The method as recited in claim 19, wherein said exhaust liner is selectively received within an outer exhaust duct, and moving one of said gas turbine engine and said exhaust liner transverse to the central longitudinal axis is performed vertically with respect to an airframe configured to receive said gas turbine engine, said exhaust liner, and said exhaust liner segment. 23. The method as recited in claim 19, wherein said turbine section includes a first turbine and a second turbine.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (11)
Moir David L. (Lake Ronkonkoma NY), Apparatus for the repair and replacement of transition ducts on jet engines and bracket therefor.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.