Variable fan duct nozzle translatable core/inner cowl including two overlapping portions made of different materials
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/00
F02K-001/08
F02K-001/06
출원번호
US-0774816
(2010-05-06)
등록번호
US-8667802
(2014-03-11)
발명자
/ 주소
West, Randall Ray
출원인 / 주소
Spirit AeroSystems, Inc.
대리인 / 주소
Hovey Williams LLP
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the a
An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.
대표청구항▼
1. A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising: a forward portion having a first front edge and a first aft edge;an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the in
1. A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising: a forward portion having a first front edge and a first aft edge;an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the inner cowl and a center axis of the inner cowl occurs at or forward of a location in which the forward portion and the aft portion meet or overlap;an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction to decrease an exit area between the inner and outer cowl; anda first inner cowl half and a second inner cowl half, each comprising: a top edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to pivotally attach to opposing sides of a pylon, anda bottom edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to mechanically fasten and unfasten with each other. 2. The inner cowl of claim 1, wherein the actuator further comprises at least one top edge actuator located proximate the top edge, the first aft edge, and the second forward edge, and at least one bottom edge actuator located proximate the bottom edge, the first aft edge, and the second forward edge, wherein the top edge actuator and the bottom edge actuator each comprise the first element and the second element. 3. The inner cowl of claim 1, wherein part of the forward portion proximate the first aft edge transitions from a first thickness down to a second thickness smaller than the first thickness and a section having the second thickness overlaps a section of the aft portion proximate the second front edge. 4. The inner cowl of claim 1, wherein the forward portion is made of a different material than the aft portion. 5. The inner cowl of claim 1, further comprising a heat-resistant panel located inward of the forward and aft portions and configured for shielding the forward and aft portions from engine heat. 6. The inner cowl of claim 5, wherein the heat-resistant panel is spaced apart from the forward and aft portions. 7. The inner cowl of claim 1, wherein the forward portion is made of a different material than the aft portion. 8. An aircraft nacelle comprising: an outer cowl having a forward end, an aft end, an outer wall, and an inner wall;an inner cowl located inward of the outer cowl, forming an air flow path therebetween, wherein the inner cowl comprises:a forward portion made of a first type of material and having a first front edge, a first aft edge;an aft portion made of a second type of material and having a second front edge and a second aft edge, wherein at least part of the forward portion proximate the first aft edge or at least part of the aft portion proximate the second front edge substantially overlaps one of the forward portion and the aft portion; andan actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction. 9. The nacelle of claim 8, wherein the aft portion is translatable aftward from a first position to a second position, wherein an aft opening between the outer cowl and the inner cowl has a smaller exit area when the aft portion is in the second position than when the aft portion is in the first position. 10. The nacelle of claim 9, wherein a vertical distance between the aft end of the outer cowl and the aft portion of the inner cowl is smaller when the aft portion is in the second position than when the aft portion is in the first position, wherein the vertical distance is measured along a line perpendicular with a center axis of the nacelle. 11. The nacelle of claim 8, wherein a radial distance between the first front edge and a center axis of the nacelle is smaller than a radial distance between the first aft edge and the center axis; wherein a radial distance between the second front edge and the center axis of the nacelle is larger than a radial distance between the second aft edge and the center axis. 12. The nacelle of claim 8, wherein a largest radial distance between the inner cowl and a center axis of the nacelle occurs at or forward of a location in which the forward portion and the aft portion overlap. 13. The nacelle of claim 8, wherein the forward portion proximate the first aft end transitions from a first thickness down to a second thickness smaller than the first thickness such that a section having the second thickness overlaps a section of the aft portion proximate the second front edge. 14. The nacelle of claim 8, further comprising a heat-resistant panel located inward of the forward and aft portions and configured for shielding the forward and aft portions from engine heat. 15. The nacelle of claim 14, wherein the heat-resistant panel is spaced apart from the forward and aft portions such that air may flow between the heat-resistant panel and the forward and aft portions in a forward-to-aft direction. 16. The nacelle of claim 15, wherein the first aft edge overlaps and is spaced a distance apart from the aft portion of the inner cowl such that air may flow in a forward-to aft direction therebetween. 17. The nacelle of claim 8, wherein the first type of material is resistant to a first amount of heat, the second type of material is resistant to a second amount of heat, and the first amount of heat is less than the second amount of heat. 18. A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising: a forward portion having a first front edge and a first aft edge;an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the inner cowl and a center axis of the inner cowl occurs at or forward of a location in which the forward portion and the aft portion meet or overlap;an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction to decrease an exit area between the inner and outer cowl; anda heat-resistant panel located inward of the forward and aft portions and configured for shielding the forward and aft portions from engine heat. 19. The inner cowl of claim 18, wherein part of the forward portion proximate the first aft edge transitions from a first thickness down to a second thickness smaller than the first thickness and a section having the second thickness overlaps a section of the aft portion proximate the second front edge. 20. The inner cowl of claim 18, wherein the heat-resistant panel is spaced apart from the forward and aft portions.
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이 특허에 인용된 특허 (10)
Migliaro, Jr., Edward F., Core cowl airfoil for a gas turbine engine.
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