Variable area fan nozzle with wall thickness distribution
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/82
F02K-001/06
출원번호
US-0834123
(2013-03-15)
등록번호
US-9394852
(2016-07-19)
발명자
/ 주소
Atassi, Oliver V.
Petrenko, Oleg
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
30
초록▼
A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan na
A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN.
대표청구항▼
1. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section;a fan nacelle around the fan, and a bypass passage extending between the fan nacelle a
1. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section;a fan nacelle around the fan, and a bypass passage extending between the fan nacelle and the core engine; anda variable area fan nozzle (VAFN) extending at least partially around the central axis and defining an exit area of the bypass passage, the VAFN being selectively movable to vary the exit area, the VAFN including a body defining an airfoil cross-section shape, the VAFN including a wall having an undulating profile, anda smoothing layer in contact with at least the undulating profile, a thickness of the smoothing layer varying inversely with the undulating profile such that an exterior of the smoothing layer over the undulating profile has a non-undulating profile,wherein the undulating profile creates a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN. 2. The gas turbine engine as recited in claim 1, wherein the first wall is a composite material. 3. The gas turbine engine as recited in claim 1, wherein the first wall includes a metallic alloy. 4. The gas turbine engine as recited in claim 1, wherein the first wall includes an aluminum alloy. 5. The gas turbine engine as recited in claim 1, wherein the mechanical property distribution is from a variation in material chemical composition of the first wall. 6. The gas turbine engine as recited in claim 1, wherein the mechanical property distribution is from a variation in material macro- or micro-structure of the first wall. 7. The gas turbine engine as recited in claim 1, wherein the first wall has ribs defining the mechanical property distribution. 8. The gas turbine engine as recited in claim 1, wherein the first wall includes a fiber-reinforced composite and a configuration of the fibers defines the mechanical property distribution. 9. The gas turbine engine as recited in claim 1, wherein the first wall includes a cured polymeric material and a variation in curing of the cured polymeric material defines the mechanical property distribution. 10. The gas turbine engine as recited in claim 1, wherein the wall is formed of a first, high modulus material and the smoothing layer is made of a second, low modulus material. 11. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section;a fan nacelle around the fan, and a bypass passage extending between the fan nacelle and the core engine; anda variable area fan nozzle (VAFN) extending at least partially around the central axis and defining an exit area of the bypass passage, the VAFN being selectively movable to vary the exit area, the VAFN including a body defining an airfoil cross-section shape, the VAFN including a first wall and a second wall,the first wall including an undulating profile, anda smoothing layer in contact with at least the undulating profile, a thickness of the smoothing layer varying inversely with the undulating profile such that an exterior of the smoothing layer over the undulating profile has a non-undulating profile,wherein the undulating profile forms a wall stiffness distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN, wherein the first wall, inclusive of the wall stiffness distribution, is radially spaced apart from the second wall. 12. The gas turbine engine as recited in claim 11, wherein the wall stiffness distribution is from a variation in at least one of a material chemical composition of the first wall and a variation in material macro- or micro-structure of the wall. 13. The gas turbine engine as recited in claim 11, wherein the first wall has ribs defining the wall stiffness distribution. 14. The gas turbine engine as recited in claim 11, wherein the first wall includes a fiber-reinforced composite and a configuration of the fibers defines the wall stiffness distribution. 15. The gas turbine engine as recited in claim 11, wherein the first wall includes a cured polymeric material and a variation in curing of the cured polymeric material defines the wall stiffness distribution. 16. The gas turbine engine as recited in claim 11, wherein the first wall has a wall thickness distribution having local thick portions and local thin portions defining the wall stiffness distribution. 17. The gas turbine engine as recited in claim 11, wherein the first wall is formed of a first, high modulus material and the smoothing layer is formed of a second, low modulus material. 18. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section;a fan nacelle around the fan, and a bypass passage extending between the fan nacelle and the core engine; anda variable area fan nozzle (VAFN) extending at least partially around the central axis and defining an exit area of the bypass passage, the VAFN being selectively movable to vary the exit area, the VAFN including a body defining an airfoil cross-section shape, the VAFN including a wall having an undulating profile, anda smoothing layer in contact with at least the undulating profile, a thickness of the smoothing layer varying inversely with the undulating profile such that an exterior of the smoothing layer over the undulating profile has a non-undulating profile,wherein the undulating profile forms a wall thickness distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN. 19. The gas turbine engine as recited in claim 18, wherein the flutter characteristic includes an amount and location of flutter on the VAFN. 20. The gas turbine engine as recited in claim 18, wherein the wall is a composite material. 21. The gas turbine engine as recited in claim 18, wherein the wall is formed of a first, high modulus material and the smoothing layer is formed of a second, low modulus material.
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이 특허에 인용된 특허 (30)
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