Apparatus and method of operating a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/00
F02G-003/00
B01D-039/00
F01D-017/16
F01D-017/02
F02C-009/22
F02C-007/05
출원번호
US-0870177
(2010-08-27)
등록번호
US-8869537
(2014-10-28)
우선권정보
GB-0917319.6 (2009-10-05)
발명자
/ 주소
Geis, Torsten
Brook, Edward
출원인 / 주소
Rolls-Royce PLC
대리인 / 주소
Oliff PLC
인용정보
피인용 횟수 :
5인용 특허 :
7
초록▼
A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts,
A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavorable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.
대표청구항▼
1. A method of operating a gas turbine engine, the gas turbine engine having a combustor, a control system, variable compressor vanes, at least one compressor bleed valve, a shaft and an anti-icing device, the method comprising: detecting impacts of particles on a surface of the gas turbine engine o
1. A method of operating a gas turbine engine, the gas turbine engine having a combustor, a control system, variable compressor vanes, at least one compressor bleed valve, a shaft and an anti-icing device, the method comprising: detecting impacts of particles on a surface of the gas turbine engine or a surface of an associated aircraft;recording the impacts;comparing the impacts of the particles with one or more stored impacts; whereinthe one or more stored impacts correspond to unfavorable weather conditions; andthe one or more stored impacts correspond to one or more impacts of rain drops, hail stones, ice particles or ice crystals;determining if the impacts of the particles matches the one or more stored impacts; andsending a signal to the control system for the gas turbine engine to adjust at least one of a position of the variable compressor vanes, a position of the at least one compressor bleed valve, a speed of rotation of the shaft, or to provide anti-icing, in order to provide sufficient surge margin for a compressor, to prevent combustor flame out, to prevent damage to compressor rotor blades, or to prevent damage to compressor stator vanes, respectively, such that the gas turbine engine operates in a safe mode of operation when it is determined that the impacts of the particles matches the one or more stored impacts. 2. The method as claimed in claim 1, the method further comprising: detecting the impacts of the particles by detecting a sound of the impacts of particles on the surface of the gas turbine engine or the surface of the associated aircraft;recording the sound of the impacts of the particles;analysing the sound of the impacts of the particles in terms of frequency, amplitude and time;comparing the sound of the impacts of the particles with the one or more stored sounds of impacts,determining if the sound of the impacts of the particles matches the one or more stored sounds of impacts. 3. The method as claimed in claim 2, wherein the analysing comprises digital signal analysis or analogue signal analysis. 4. The method as claimed in claim 3, wherein the analysing comprises performing a fast Fourier transformation. 5. The method as claimed in claim 2, further comprising detecting the particles with at least one microphone. 6. The method as claimed in claim 1, further comprising detecting impacts of particles on a surface selected from the group comprising an outer surface of a nacelle, a surface of blade, a surface of a vane, a surface of an inlet, a surface of a wing and a surface of a fuselage. 7. The method as claimed in claim 6, further comprising detecting impacts of particles on a variable vane or a fixed vane. 8. The method as claimed in claim 6, further comprising detecting impacts of particles on a fan blade or a compressor blade. 9. The method as claimed in claim 1, further comprising detecting a change in pressure caused by direct impacts of the particles. 10. The method as claimed in claim 1, further comprising detecting a change in pressure in the air caused by the impacts of the particles. 11. The method as claimed in claim 1, wherein the gas turbine engine is operating at low power settings during flight, the method further comprising sending a signal to the control system to increase the power setting and/or open the at least one compressor bleed valve to provide sufficient surge margin for the compressor if heavy rain or hail is detected. 12. The method as claimed in claim 1, wherein the gas turbine engine is operating at idle power settings during flight, the method further comprising sending a signal to the control system to increase the idle power setting and/or open the at least one compressor bleed valve to provide sufficient surge margin for the compressor. 13. A gas turbine engine and an apparatus for operating the gas turbine engine, the gas turbine engine having a combustor, a control system, variable compressor vanes, at least one compressor bleed valve a shaft and an anti-icing device, the apparatus comprising: at least one detector to detect impacts of particles on a surface of the gas turbine engine or a surface of an associated aircraft;a recorder to record the impacts;a store of one or more stored impacts; whereinthe one or more stored impacts correspond to unfavorable weather conditions; andthe one or more stored impacts correspond to one or more impacts of rain drops, hail stones, ice particles or ice crystals;a comparator to compare the impacts of particles with the one or more impacts stored in the store of impacts, the comparator being arranged to send a signal to a control system for the gas turbine engine to adjust at least one of a position of the variable compressor vanes, a position of the at least one compressor bleed valve, a speed of rotation of the shaft, or to provide anti-icing, in order to provide sufficient surge margin for a compressor, to prevent combustor flame out, to prevent damage to compressor rotor blades, or to prevent damage to compressor stator vanes, respectively, such that the gas turbine engine operates in a safe mode of operation when it is determined that the impacts of the particles matches the one or more stored impacts. 14. The gas turbine engine as claimed in claim 13, wherein the at least one detector detects a sound of the impacts of the particles on the surface of the gas turbine engine or the surface of the associated aircraft;the recorder records the sound of the impacts of the particles;the analyser analyses the sound of the impacts of the particles in terms of frequency, amplitude and time;the store of impacts stores the sound of the impacts, the one or more stored sounds of impacts corresponding one or more impacts of rain drops, hail stones, ice particles or ice crystals;the comparator compares the sound of the impacts of the particles with the one or more sounds of impacts stored in the store of sounds of impacts. 15. The gas turbine engine as claimed in claim 14, wherein the analyser is a digital signal analyser or an analogue signal analyser. 16. The gas turbine engine as claimed in claim 15, wherein the analyser is arranged to perform a fast Fourier transformation. 17. The gas turbine engine as claimed in claim 14, wherein the at least one detector is a microphone. 18. The gas turbine engine as claimed in claim 13, wherein the at least one detector is arranged to detect impacts of particles on a surface selected from the group comprising an outer surface of a nacelle, a surface of blade, a surface of a vane, a surface of an inlet, a surface of a wing and a surface of a fuselage. 19. The gas turbine engine as claimed in claim 18, wherein the vane is selected from the group comprising a variable vane and a fixed vane. 20. The gas turbine engine as claimed in claim 18, wherein the blade is selected from the group comprising a fan blade and a compressor blade. 21. The gas turbine engine as claimed in claim 13, wherein the gas turbine engine is selected from the group comprising a turbofan, a turbojet and a turbo-propeller. 22. The gas turbine engine as claimed in claim 13, wherein the at least one detector is arranged to detect a change in pressure caused by direct impact of the particles. 23. The gas turbine engine as claimed in claim 13, wherein the at least one detector is arranged to detect a change in pressure in the air caused by the impacts of the particles.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (7)
Smith David M. ; Dorris ; III John, Aircraft engine apparatus with reduced inlet vortex.
Visser, Nicholas; Adibhatla, Sridhar; Lax, David Michael, Enhancing engine performance to improve fuel consumption based on atmospheric rain conditions.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.