Gas turbine engines having plasma flow-controlled intake systems
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/14
F04D-029/22
F04D-029/68
B64C-021/04
F15D-001/00
F02C-007/057
출원번호
US-0898275
(2013-05-20)
등록번호
US-9359950
(2016-06-07)
발명자
/ 주소
Matwey, Mark
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Ingrassia Fisher & Lorenz, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion
Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.
대표청구항▼
1. A Gas Turbine Engine (“GTE”), comprising: a turbine section; a combustion section upstream of the turbine section; a compressor section upstream of the combustion section; and an intake section upstream of the compressor section, the intake section comprising: a plenum; a first inlet fluidly coup
1. A Gas Turbine Engine (“GTE”), comprising: a turbine section; a combustion section upstream of the turbine section; a compressor section upstream of the combustion section; and an intake section upstream of the compressor section, the intake section comprising: a plenum; a first inlet fluidly coupled to the plenum; a centerbody projecting into the plenum and having an outer surface impinged by airflow directed into the plenum through the first inlet during operation of the GTE; an outer plenum wall circumscribing the plenum, the first inlet formed through the outer plenum wall at a first location radially overlapping with the centerbody; a first array of plasma actuators disposed on the centerbody and, when activated, suppressing vortex shedding of air flowing over and around the outer surface, the first array of plasma actuators positioned substantially opposite a second location at which airflow impinged the centerbody when directed into the plenum through the first inlet. 2. The GTE of claim 1 wherein the centerbody is substantially co-axial with the centerline of the GTE. 3. The GTE of claim 2 wherein the centerline of first inlet is substantially perpendicular to longitudinal axis of centerbody. 4. The GTE of claim 2 further comprising: a housing assembly enclosing the turbine section, the combustion section, the compressor section, and the intake section; anda shaft rotatably mounted in the housing assembly and extending through the centerbody. 5. The GTE of claim 4 further comprising a forward bearing assembly supporting the shaft and disposed within the centerbody. 6. The GTE of claim 2 wherein the outer surface is conical. 7. The GTE of claim 5 wherein a maximum outer diameter of the centerbody is greater than one eighth a maximum inner diameter of the plenum and less than the maximum inner diameter of the plenum. 8. The GTE of claim 5 wherein an outer diameter of the centerbody decreases in a fore-aft direction, and wherein the intake section further comprises an outer circumferential wall bounding an outer circumference of the plenum and increasing in diameter in the fore-aft direction. 9. The GTE of claim 8 wherein a forward circumferential edge portion of the centerbody and a forward end portion of the outer circumferential wall converge in the aft-fore direction. 10. The GTE of claim 1 wherein the intake section further comprises: a second inlet fluidly coupled to the plenum; and a second array of plasma actuators disposed on the centerbody. 11. The GTE of claim 10 wherein the first inlet is an open loop inlet, and wherein the second inlet is a closed loop inlet. 12. The GTE of claim 10 further comprising a controller operably coupled to the first array of plasma actuators and the second array of plasma actuators and configured to: (i) activate the first array of plasma actuators when airflow is directed into the plenum through the first inlet, and (ii) activate the second array of plasma actuators when airflow is directed into the plenum through the second inlet. 13. The GTE of claim 12 wherein the controller is further configured to: (i) deactivate the first array of plasma actuators, if active, when airflow through the first inlet ceases, and (ii) deactivate the second array of plasma actuators, if active, when airflow through the first inlet ceases. 14. The GTE of claim 2 wherein the compressor section comprises a compressor, and wherein the aft end of centerbody terminates adjacent a forward end of the compressor. 15. The GTE of claim 1 wherein the first array of plasma actuators generates plasma fields when activated, and wherein the first array of plasma actuators is positioned such that the plasma fields point toward a third location on the centerbody that is substantially diametrically opposite the first inlet. 16. A Gas Turbine Engine (“GTE”), comprising: a turbine section; a combustion section upstream of the turbine section; a compressor section upstream of the combustion section; an intake section upstream of the compressor section, the intake section comprising: an intake assembly housing having first and second sidewall inlets; a centerbody disposed within the intake assembly housing and impinged by airflow received through the first and second sidewall inlets; a first plasma actuator array mounted on the centerbody at a first location substantially opposite the first sidewall inlet; and a second plasma actuator array mounted on the centerbody at a second location substantially opposite the second sidewall inlet; and a controller operably coupled to the first and second plasma actuator arrays, the controller configured to active (i) the first plasma actuator array when airflow is received through the first sidewall inlet, and (ii) the second plasma actuator array when airflow is received through the second sidewall inlet. 17. The GTE of claim 16 wherein at least a portion of the first plasma actuator array and the second plasma actuator array overlap. 18. A plasma flow-controlled intake system for deployment on a gas turbine engine having an intake section, the intake section comprising a plenum, a first inlet fluidly coupled to the plenum, a second inlet fluidly coupled to the plenum, and a centerbody disposed within the plenum and impinged by airflow delivered into the plenum through the first inlet and the second inlets, the gas turbine engine operable in a first operational mode wherein airflow is directed into the plenum through the first inlet and a second operational mode wherein the airflow is directed into the plenum through the second inlet, the plasma flow-controlled intake system further comprising: a first array of plasma actuators disposed on the centerbody; and a second array of plasma actuators disposed on the centerbody; a controller coupled to the first and second arrays of plasma actuators, the controller activating the first array of plasma actuators when the gas turbine engine operates in the first operational mode and activating the second array of plasma actuators when the gas turbine engine operates in the second operational mode to suppress vortex shedding of airflowing over an outer surface of the centerbody. 19. The plasma flow-controlled intake system of claim 18 wherein the first array of plasma actuators is disposed on the centerbody at a location substantially opposite the first inlet.
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Silkey, Joseph S.; Wilson, Christopher D.; Dyer, Richard S., Inlet distortion and recovery control system.
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