Inlet guide vanes and gas turbine engine systems involving such vanes
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-017/12
F02C-009/22
F01D-005/14
F01D-017/16
출원번호
US-0344942
(2008-12-29)
등록번호
US-9249736
(2016-02-02)
발명자
/ 주소
Carroll, Christian A.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
5인용 특허 :
16
초록▼
Inlet guide vanes and gas turbine engine systems involving such vanes are provided, In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut
Inlet guide vanes and gas turbine engine systems involving such vanes are provided, In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other.
대표청구항▼
1. An inlet guide vane for a gas turbine engine comprising: a fixed strut; anda variable flap located downstream of the fixed strut and being movable with respect thereto;the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge
1. An inlet guide vane for a gas turbine engine comprising: a fixed strut; anda variable flap located downstream of the fixed strut and being movable with respect thereto;the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being assymetric with respect to each other, a trailing portion of the side surface of the fixed strut located adjacent to a suction surface of the variable flap is operative to turn gas flow between approximately 0.5 degrees and approximately 10 degrees prior to the gas flow reaching the variable flap. 2. The inlet guide vane of claim 1, wherein the trailing portion of the side surface of the fixed strut is operative to turn the gas flow between approximately 1 and degree approximately 5 degrees prior to the gas flow reaching the variable flap. 3. The inlet guide vane of claim 1, wherein upstream portions of the side surfaces of the fixed strut exhibit symmetry. 4. The inlet guide vane of claim 1, wherein the fixed strut exhibits a negative camber in a vicinity of the trailing edge. 5. The inlet guide vane of claim 4, wherein the negative camber begins at between approximately 25% and approximately 95% chord of the fixed strut. 6. The inlet guide vane of claim 5, wherein the negative camber begins at between approximately 50% and approximately 80% chord of the fixed strut. 7. The inlet guide vane of claim 1, wherein: the variable flap has a suction side and a pressure side;the variable flap is movable between a nominal position, at which a minimum deflection is imparted to gas flowing over the variable flap, and a maximum deflected position, at which a maximum deflection is imparted to gas flowing over the variable flap; andin the nominal position, the suction side is not masked by the fixed strut. 8. The inlet guide vane of claim 7, wherein, in the maximum deflected position, the suction side is masked by the fixed strut. 9. The inlet guide vane of claim 7, wherein: the variable flap is movable through a range of deflected positions between the nominal position and the maximum deflected position; andthroughout the range of deflected positions, the suction side is not masked by the fixed strut. 10. The inlet guide vane of claim 1, wherein a thickness of the fixed strut at the trailing edge is between approximately 90% and approximately 50% of a maximum thickness of the variable flap. 11. The inlet guide vane of claim 1, wherein: the variable flap is movable through a range of deflected positions between a nominal position and a maximum deflected position; andresponsive to the variable flap being positioned in at least one of the deflected positions, the asymmetry of the side surfaces of the fixed strut is operative to turn gas flowing over one of the side surfaces of the fixed strut prior to the gas reaching the variable flap such that the turn provided by the asymmetry assists in turning of the gas accomplished by the position of the variable flap. 12. The inlet guide vane of claim 1, wherein: the variable flap is movable through a range of deflected positions between a nominal position and a maximum deflected position; andthe asymmetry exhibited by the fixed strut reduces a tendency of gas flowing along the side surfaces of the fixed strut to separate from the inlet guide vane. 13. A gas turbine engine comprising: a compressor section having an inlet guide vane assembly, a set of rotatable blades and a set of stationary vanes;the inlet guide vane assembly being located upstream of the set of rotatable blades and the set of stationary vanes, the inlet guide vane assembly having multiple guide vanes;a first of the guide vanes having a fixed strut and a variable flap, the variable flap being located downstream of the fixed strut and being movable with respect thereto, the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other, a trailing portion of the side surface of the fixed strut located adjacent to a suction surface of the variable flap is operative to turn gas flow between approximately 0.5 degrees and approximately 10 degrees prior to the gas flow reaching the variable flap. 14. The gas turbine engine of claim 13, wherein the inlet guide vane assembly is an inlet guide vane assembly for a low pressure compressor. 15. The gas turbine engine of claim 13, wherein the gas turbine engine is a turbojet.
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이 특허에 인용된 특허 (16)
Lawer Steven D. (Derby GB2), Actuator mechanism for variable angle vane arrays.
Capozzi, Joseph; Zenon, Ruby Lasandra; Turner, Alan Glen; Wallis, Carol Vaczy; Szucs, Peter Nicholas, Methods and apparatus for varying gas turbine engine inlet air flow.
Amos David J. (Wallingford PA) Ichiryu Taku (Kakogawa JA) Sato Tomohiko (Kobe JA), Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine.
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