Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/12
F23R-003/16
출원번호
US-0483499
(2012-05-30)
등록번호
US-9163582
(2015-10-20)
발명자
/ 주소
Treat, Christopher
Stenman, Christina A.
Duelm, Shelton O.
Simpson, Alex J.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
17
초록▼
A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plur
A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.
대표청구항▼
1. A liner assembly comprising: a plurality of flaps arranged about a central axis and that are operable to move relative to the central axis,each of the plurality of flaps defining a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis, a
1. A liner assembly comprising: a plurality of flaps arranged about a central axis and that are operable to move relative to the central axis,each of the plurality of flaps defining a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis, andeach of the plurality of flaps having a thickness between the inner surface and the outer surface, the thickness varying in a lateral direction between the lateral sides, wherein each of the plurality of flaps includes at least one respective trough that is elongated in an axial direction with regard to a flap central axis extending between the forward end and the aft end. 2. The assembly as recited in claim 1, wherein each of the plurality of flaps is a ceramic matrix composite having a ceramic matrix and a reinforcement phase dispersed through the ceramic matrix. 3. The assembly as recited in claim 1, wherein each of the plurality of flaps is an organic matrix composite having an organic matrix and a reinforcement phase dispersed through the organic matrix. 4. The assembly as recited in claim 1, wherein the at least one trough extends entirely from the forward end to the aft end. 5. The assembly as recited in claim 1, wherein the at least one trough is located in a lateral central region of the respective one of the plurality of flaps. 6. The assembly as recited in claim 1, wherein each of the plurality of flaps includes a minimum thickness t1 and a maximum thickness t2 such that a ratio of t2/t1 is in a range of 1.4 to 3. 7. The assembly as recited in claim 1, wherein each of the plurality of flaps is laterally spaced apart neighboring ones of the plurality of flaps. 8. The assembly as recited in claim 1, wherein the inner surface is planar and the outer surface is non-planar. 9. An engine comprising: a compressor section;a combustor section in communication with the compressor section; anda liner in communication with the combustor section, the liner including a plurality of flaps arranged about a central axis and that are operable to move relative to the central axis, each of the plurality of flaps defining a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis, each of the plurality of flaps having a thickness between the inner surface and the outer surface, the thickness varying in a lateral direction between the lateral sides, wherein each of the plurality of flaps includes a thin section and first and second thick sections, relative to the thin section, that laterally bound the thin section. 10. The engine as recited in claim 9, wherein the thin section has a lateral width w1 in the lateral direction and each of the first and second thick sections has a lateral width w2 in the lateral direction such that a ratio of (w1+w2)/w1 is in a range of 2 to 11. 11. The engine as recited in claim 9, wherein the thin section has a lateral width w1 in the lateral direction and each of the first and second thick sections has a lateral width w2 in the lateral direction such that a ratio of (w1+w2)/w1 is in a range of 3.19 to 6.7. 12. The engine as recited in claim 9, wherein the first and second thick sections are of equal thickness. 13. The engine as recited in claim 9, wherein the first and second thick sections are symmetric with regard to a flap central axis extending between the forward end and the aft end. 14. A liner assembly comprising: a plurality of flaps arranged about a central axis and that are operable to move relative to the central axis,each of the plurality of flaps defining a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis, andeach of the plurality of flaps having a thickness between the inner surface and the outer surface, the thickness varying in a lateral direction between the lateral sides, wherein each of the plurality of flaps includes a thin section and first and second thick sections, relative to the thin section, that laterally bound the thin section. 15. The assembly as recited in claim 14, wherein the thin section has a lateral width w1 in the lateral direction and each of the first and second thick sections has a lateral width w2 in the lateral direction such that a ratio of (w1+w2)/w1 is in a range of 2 to 11. 16. The assembly as recited in claim 14, wherein the thin section has a lateral width w1 in the lateral direction and each of the first and second thick sections has a lateral width w2 in the lateral direction such that a ratio of (w1+w2)/w1 is in a range of 3.19 to 6.7. 17. The assembly as recited in claim 14, wherein the first and second thick sections are of equal thickness. 18. The assembly as recited in claim 14, wherein the first and second thick sections are symmetric with regard to a flap central axis extending between the forward end and the aft end. 19. The assembly as recited in claim 14, further comprising first and second inclined surfaces, relative to the inner surface and the outer surface, the first and second inclined surfaces joining the respective first and second thick sections with the thin section.
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이 특허에 인용된 특허 (17)
Lippmeier William C., Articulated exhaust nozzle fairing.
McLafferty George H. (North Palm Beach FL) Thayer Edward B. (Palm Beach Garden FL) Stewart Jim D. (Sebastian FL), Axisymmetric nozzle with gimbled unison ring.
Luffy Ronald J. (Maineville OH) Taylor ; Jr. John B. (Cincinnati OH) Sutherland William V. (Milford OH) Stine Frederick J. (Mainville OH) Crowley James A. (Midlothian VA) Mann David E. (West Chester , Method and apparatus for boosting ram airflow to an ejection nozzle.
Osga, Kyle J.; Krystowski, Edward A., Thermally compliant rivet connection for connecting turbine engine liner to convergent flap and seal for turbine nozzle.
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