Axisymmetric nozzles of variable geometry and orientation of the flow which are intended for gas turbine engines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-015/00
출원번호
US-0319288
(1994-10-06)
우선권정보
ES-0001114 (1994-05-20)
발명자
/ 주소
Zubillaga Mikel G. (Hernani ESX) Urruela Jose R. (Las Arenas ESX)
출원인 / 주소
Sener, Ingenieria Y Sistemas, S.A. (ESX 03)
인용정보
피인용 횟수 :
11인용 특허 :
0
초록▼
Improvements in orientable axisymmetric nozzles of variable geometry which are intended for gas turbine engines, which nozzles comprise a convergent zone (2) followed by a divergent zone (3), both formed by main petals (4-5) and secondary petals (33-34), and they add to the known functions (simultan
Improvements in orientable axisymmetric nozzles of variable geometry which are intended for gas turbine engines, which nozzles comprise a convergent zone (2) followed by a divergent zone (3), both formed by main petals (4-5) and secondary petals (33-34), and they add to the known functions (simultaneous axisymmetric variation, according to a preestablished law, of the throat area A8 and of the outlet area A9; variation of all the geometry of the outlet area A9 independently of the throat area A8; and, axisymmetric orientation of the flow) a fourth function of varying only a part of the geometry of the outlet area A9 independently of the throat area A8.
대표청구항▼
A thrust vectoring variable geometry axisymmetric exhaust nozzle for a gas turbine engine having a direction of gas flow, which comprises: a convergent zone defining a throat of variable are followed, in the direction of gas flow, by a divergent zone, the convergent zone including convergent main pe
A thrust vectoring variable geometry axisymmetric exhaust nozzle for a gas turbine engine having a direction of gas flow, which comprises: a convergent zone defining a throat of variable are followed, in the direction of gas flow, by a divergent zone, the convergent zone including convergent main petals and convergent secondary petals supported on adjacent convergent main petals, the divergent zone including divergent main petals and divergent secondary petals supported on adjacent divergent main petals and connected to the adjacent divergent main petals by a centering mechanism, the petals of said convergent and divergent zones being distributed circumferentially about a longitudinal axis of the engine; the convergent and divergent main petals are joined together by tangential cylindrical linkages having axes perpendicular to the longitudinal axis of the engine; each divergent main petal is transversely subdivided into two segments, the upstream and the downstream segment, joined together by cylindrical linkages having an axis perpendicular to the tangential linkage between the convergent main petal and the divergent main petal; control means for regulating the throat area and vectoring of the thrust comprising internal, intermediate and external rings concentric to each other and with the centerline of the engine, and a plurality of linear actuators having upstream and downstream ends, and a mechanism for regulating the throat area; the main convergent petals being linked to the internal ring by cylindrical articulations; a set of two-hinged bars, one for each divergent main petal, interconnecting the downstream segment of the divergent main petals with the external ring, a plurality of control actuators articulated at their upstream end to a fixed structure of the engine, some of the control actuators articulated at their downstream end to external ring spherical linkages and the other control actuators articulated at their downstream end to intermediate ring spherical linkages, thrust vectoring being achieved in the divergent zone by inclination of the external ring with a center of tilting on the longitudinal axis of the engine through the set of two-hinged bars; each of the rings being independently connected to the fixed structure of the engine by support means, which do not interconnect them, maintaining each ring laterally fixed; the external ring including two external ring segments which are mutually articulated by a pair of spindles for varying symmetrically, by a simultaneous and opposite direction tilting of the two external ring segments, the outlet area with respect to an immobilized throat area, and during vectorization of the gas flow, by an independent tilting of one of the two external ring segments, correcting the outlet area asymmetrically while the other external ring segment remains immobilized.
Urruela Jose Rivacoba,ESX ; Aldecoa-Otalora Kepa M.,ESX, Variable geometry axisymmetric nozzle with 2-d thrust vectoring intended for a gas turbine engine.
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