IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0775649
(2010-05-07)
|
등록번호 |
US-8286654
(2012-10-16)
|
발명자
/ 주소 |
- Prasad, Dilip
- Feng, Jinzhang
- Sabnis, Jayant S.
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
Carlson, Gaskey & Olds PC
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
17 |
초록
▼
A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner,
A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.
대표청구항
▼
1. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface defining an inlet duct having a flow area; andan actuator disposed in said inner nacelle surface for selectively reducing said flow area to
1. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface defining an inlet duct having a flow area; andan actuator disposed in said inner nacelle surface for selectively reducing said flow area to increase the Mach number of air into said gas turbine engine to enhance acoustic attenuation associated with said inlet duct, wherein said actuator comprises an inflatable bladder disposed in said nacelle and having an inflated state wherein said inflatable bladder protrudes into said flow area of said inlet duct, and, in said inflated state, a portion of said inflatable bladder disposed in an upper portion of said inlet duct has a smaller protrusion into said flow area relative to a portion of said inflatable bladder disposed at a lower portion of said inlet duct. 2. The gas turbine engine of claim 1 wherein said inner nacelle surface is downstream of a leading edge. 3. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface defining an inlet duct having a flow area; andan actuator disposed in said inner nacelle surface for selectively reducing said flow area to increase the Mach number of air into said gas turbine engine to enhance acoustic attenuation associated with said inlet duct, wherein said actuator comprises an inflatable bladder disposed in said nacelle which, when inflated reduce said flow area of said inlet duct, and wherein said inflatable bladder is segmented around said circumference of said nacelle to allow asymmetrical deployment thereof. 4. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface;a spinner disposed on said fan section such that said inner nacelle surface and said spinner defines an inlet duct; anda shape memory alloy actuator disposed in said spinner said shape memory alloy actuator including a compliant surface moveable between a distended position into said inlet duct and a retracted position withdrawn from said inlet duct. 5. The gas turbine engine of claim 4 further comprising a multiple of fan blades which extend from said spinner. 6. The gas turbine engine of claim 4, wherein said shape memory alloy actuator includes a plurality of shape memory alloy members located radially outwards of said compliant surface. 7. The gas turbine engine of claim 6, wherein said plurality of shape memory alloy members comprise rings. 8. The gas turbine engine of claim 6, wherein said plurality of shape memory alloy members comprise ropes. 9. The gas turbine engine of claim 6, wherein in said distended position said shape memory alloy actuator asymmetrically protrudes into said inlet duct. 10. A gas turbine engine comprising: a nacelle enclosing a fan section, a compressor, a combustor and a turbine, said nacelle including an inner nacelle surface defining an inlet duct having a flow area; anda shape memory alloy actuator including shape memory alloy members located adjacent a compliant surface bounding said flow area, said compliant surface including a distended position extending into said flow area and a retracted position withdrawn from said flow area.
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