Control apparatus for estimating operating parameter of a gas-turbine aeroengine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/18
F02C-003/107
출원번호
US-0689298
(2015-04-17)
등록번호
US-9903278
(2018-02-27)
발명자
/ 주소
Okada, Taizo
출원인 / 주소
HONDA MOTOR CO., LTD.
대리인 / 주소
Rankin, Hill & Clark LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
An apparatus for estimating operating parameter of a gas-turbine aeroengine is configured to calculate a rotational speed of the low-pressure turbine (N1) by retrieving preset first characteristics by at least a rotational speed of the high-pressure turbine (N2), an engine inlet temperature and a fi
An apparatus for estimating operating parameter of a gas-turbine aeroengine is configured to calculate a rotational speed of the low-pressure turbine (N1) by retrieving preset first characteristics by at least a rotational speed of the high-pressure turbine (N2), an engine inlet temperature and a first amount of bled air, to calculate a compensating value (ΔN1) of the rotational speed of the low-pressure turbine by retrieving preset second characteristics by at least a second amount of bled air, and to calculate the rotational speed of the low-pressure turbine (N1) finally based on the calculated rotational speed of the low-pressure turbine (N1) and the compensating value (ΔN1) thereof.
대표청구항▼
1. An apparatus for estimating operating parameter of a gas-turbine aeroengine mounted on an aircraft and having at least a high-pressure turbine rotated by injection of high-pressure gas produced upon ignition and combustion of an air-fuel mixture in a combustion chamber, and a low-pressure turbine
1. An apparatus for estimating operating parameter of a gas-turbine aeroengine mounted on an aircraft and having at least a high-pressure turbine rotated by injection of high-pressure gas produced upon ignition and combustion of an air-fuel mixture in a combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas exiting the high-pressure turbine, comprising: a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2);an engine inlet temperature sensor adapted to detect an inlet temperature of the engine (T1);a first bleed off valve position sensor adapted to detect a first amount of bled air flowing through a high-pressure compressor connected to the high-pressure turbine and bled through a first bleed off valve;a second bleed off valve position sensor adapted to detect a second amount of bled air flowing through the high-pressure compressor connected to the high-pressure turbine and bled through a second bleed off valve;a low-pressure turbine rotational speed calculator configured to calculate a rotational speed of the low-pressure turbine (N1) by retrieving preset first characteristics by at least the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor, the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor and the first amount of bled air detected by the first bleed off valve position sensor;a low-pressure turbine rotational speed compensating value calculator configured to calculate a compensating value (ΔN1) of the rotational speed of the low-pressure turbine (N1) by retrieving preset second characteristics by at least the second amount of bled air detected by the second bleed off valve position sensor; anda final low-pressure turbine rotational speed calculator configured to calculate the rotational speed of the low-pressure turbine (N1) finally based on the rotational speed of the low-pressure turbine (N1) calculated by the low-pressure turbine rotational speed calculator and the compensating value (ΔN1) calculated by the low-pressure turbine rotational speed compensating value calculator. 2. The apparatus according to claim 1, wherein the low-pressure turbine rotational speed calculator includes: a corrected rotational speed calculator configured to calculate a corrected rotational speed of the high-pressure turbine (N2K1) corrected by the inlet temperature of the engine (T1) based on the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor, and calculates a corrected rotational speed of the low-pressure turbine (N1K1) by retrieving the preset first characteristics by at least the calculated corrected rotational speed of the high-pressure turbine (N2K1) and the first amount of bled air detected by the first bleed off valve position sensor;a first corrected rotational speed compensating value calculator configured to calculate a compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving third preset characteristics by at least a flight altitude of the aircraft (ALT); anda second corrected rotational speed compensating value calculator configured to calculate the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving fourth preset characteristics by at least a flight speed of the aircraft (Mn); andcompensates the corrected rotational speed of the low-pressure turbine (N1K1) calculated by the corrected rotational speed calculator by the compensating values (ΔN1K1) calculated by the first and second corrected rotational speed compensating value calculators. 3. The apparatus according to claim 2, wherein the low-pressure turbine rotational speed calculator includes: a third corrected rotational speed compensating value calculator configured to calculate the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving fifth preset characteristics by at least a deviation from an ISA where the aircraft locates (dISA);and compensates the corrected rotational speed of the low-pressure turbine (N1K1) calculated by the corrected rotational speed calculator by the compensating values (ΔN1K1) calculated by the first, second and third corrected rotational speed compensating value calculators. 4. The apparatus according to claim 3, wherein the low-pressure turbine rotational speed calculator includes: a transformer that inputs the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor and transforms the corrected rotational speed of the low-pressure turbine (N1K1) into the rotational speed of the low-pressure turbine (N1); andthe final low-pressure turbine rotational speed calculator is configured to calculate the rotational speed of the low-pressure turbine (N1) finally based on the rotational speed of the low-pressure turbine (N1) transformed by the transformer and the compensating value (ΔN1) calculated by the low-pressure turbine rotational speed compensating value calculator. 5. The apparatus according to claim 1, wherein the low-pressure turbine rotational speed calculator includes: a low-pressure turbine rotational speed sensor normality discriminator that discriminates whether or not a low-pressure turbine rotational speed sensor is normal by comparing the rotational speed of the low-pressure turbine (N1) detected by the low-pressure turbine rotational speed sensor with the rotational speed of the low-pressure turbine (N1) calculated by the final low-pressure turbine rotational speed calculator. 6. An apparatus for estimating operating parameter of a gas-turbine aeroengine mounted on an aircraft and having at least a high-pressure turbine rotated by injection of high-pressure gas produced upon ignition and combustion of an air-fuel mixture in a combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas exiting the high-pressure turbine, comprising: a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2);an engine inlet temperature sensor adapted to detect an inlet temperature of the engine (T1);a first bleed off valve position sensor adapted to detect a first amount of bled air flowing through a high-pressure compressor connected to the high-pressure turbine and bled through a first bleed off valve;a second bleed off valve position sensor adapted to detect a second amount of bled air flowing through the high-pressure compressor connected to the high-pressure turbine and bled through a second bleed off valve;a compressor outlet pressure calculator configured to calculate a corrected rotational speed of the high-pressure turbine (N2K1) corrected by the inlet temperature of the engine (T1) based on the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor, and configured to calculate an outlet pressure of the high-pressure compressor (P3) by retrieving preset first characteristics by at least the calculated corrected rotational speed of the high-pressure turbine (N2K1) and the first amount of bled air detected by the first bleed off valve position sensor;a first compressor outlet pressure compensating value calculator configured to calculate a compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving preset second characteristics by at least the second amount of bled air detected by the second bleed off valve position sensor; anda final compressor outlet pressure calculator configured to calculate the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the compressor outlet pressure calculator and the compensating value (ΔP3) calculated by the first compressor outlet pressure 30 compensating value calculator. 7. The apparatus according to claim 6, further including: a second compressor outlet pressure compensating value calculator configured to calculate a compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving third preset characteristics by at least a flight altitude of the aircraft (ALT); anda third compressor outlet pressure compensating value calculator configured to calculate the compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving fourth preset characteristics by at least a flight speed of the aircraft (Mn);and the final compressor outlet pressure calculator is configured to calculate the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the compressor outlet pressure calculator and the compensating values (ΔP3) calculated by the first, second and third compressor outlet pressure compensating value calculators. 8. The apparatus according to claim 7, further including: a fourth compensator outlet pressure compensating value calculator configured to calculate the compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving fifth preset characteristics by at least a deviation from an ISA where the aircraft locates (dISA);and the final compressor outlet pressure calculator is configured to calculate the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the compressor outlet pressure calculator and the compensating values (ΔP3) calculated by the first, second, third and fourth compressor outlet pressure compensating value calculators. 9. The apparatus according to claim 6, further including: an engine inlet pressure sensor adapted to detect an inlet pressure of the engine (P1);and the compressor outlet pressure calculator is configured to calculate the outlet pressure of the high-pressure compressor (P3) in terms of a ratio of the outlet pressure of the high-pressure compressor (P3) relative to the detected inlet pressure of the engine (P1). 10. The apparatus according to claim 6, further including: a compressor outlet pressure sensor adapted to detect the outlet pressure of the high-pressure compressor (P3); anda compressor outlet pressure sensor normality discriminator that discriminates whether or not the compressor outlet pressure sensor is normal by comparing the outlet pressure of the high-pressure compressor (P3) detected by the compressor outlet pressure sensor with the outlet pressure of the high-pressure compressor (P3) calculated by the final compressor outlet pressure calculator. 11. A method for estimating operating parameter of a gas-turbine aeroengine mounted on an aircraft and having at least a high-pressure turbine rotated by injection of high-pressure gas produced upon ignition and combustion of an air-fuel mixture in a combustion chamber, a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas exiting the high-pressure turbine, a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2), an engine inlet temperature sensor adapted to detect an inlet temperature of the engine (T1), a first bleed off valve position sensor adapted to detect a first amount of bled air flowing through a high-pressure compressor connected to the high-pressure turbine and bled through a first bleed off valve, and a second bleed off valve position sensor adapted to detect a second amount of bled air flowing through the high-pressure compressor connected to the high-pressure turbine and bled through a second bleed off valve; comprising the steps of:calculating a rotational speed of the low-pressure turbine (N1) by retrieving preset first characteristics by at least the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor, the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor and the first amount of bled air detected by the first bleed off valve position sensor;calculating a compensating value (ΔN1) of the rotational speed of the low-pressure turbine (N1) by retrieving preset second characteristics by at least the second amount of bled air detected by the second bleed off valve position sensor; andcalculating the rotational speed of the low-pressure turbine (N1) finally based on the rotational speed of the low-pressure turbine (N1) calculated by the step of low-pressure turbine rotational speed calculating and the compensating value (ΔN1) calculated by the step of low-pressure turbine rotational speed compensating value calculating. 12. The method according to claim 11, wherein the step of low-pressure turbine rotational speed calculating includes: calculating a corrected rotational speed of the high-pressure turbine (N2K1) corrected by the inlet temperature of the engine (T1) based on the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor, and calculating a corrected rotational speed of the low-pressure turbine (N1K1) by retrieving the preset first characteristics by at least the calculated corrected rotational speed of the high-pressure turbine (N2K1) and the first amount of bled air detected by the first bleed off valve position sensor;calculating a compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving third preset characteristics by at least a flight altitude of the aircraft (ALT); andcalculating the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving fourth preset characteristics by at least a flight speed of the aircraft (Mn);and compensating the corrected rotational speed of the low-pressure turbine (N1K1) calculated by the step of corrected rotational speed calculating by the compensating values (ΔN1K1) calculated by the steps of first and second corrected rotational speed compensating value calculating. 13. The method according to claim 12, wherein the step of low-pressure turbine rotational speed calculating includes: calculating the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) by retrieving fifth preset characteristics by at least a deviation from an ISA where the aircraft locates (dISA);and compensating the corrected rotational speed of the low-pressure turbine (N1K1) calculated by the step of corrected rotational speed calculating by the compensating values (ΔN1K1) calculated by the steps of first, second and third corrected rotational speed compensating value calculating. 14. The method according to claim 13, wherein step of the low-pressure turbine rotational speed calculating includes the step of: inputting the compensating value (ΔN1K1) of the corrected rotational speed of the low-pressure turbine (N1K1) and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor and transforming the corrected rotational speed of the low-pressure turbine (N1K1) into the rotational speed of the low-pressure turbine (N1);and the step of final low-pressure turbine rotational speed calculating calculates the rotational speed of the low-pressure turbine (N1) finally based on the rotational speed of the low-pressure turbine (N1) transformed by the step of transforming and the compensating value (ΔN1) calculated by the step of low-pressure turbine rotational speed compensating value calculating. 15. The method according to claim 11, wherein the step of low-pressure turbine rotational speed calculating includes: discriminating whether or not a low-pressure turbine rotational speed sensor is normal by comparing the rotational speed of the low-pressure turbine (N1) detected by the low-pressure turbine rotational speed sensor with the rotational speed of the low-pressure turbine (N1) calculated by the step of low-pressure turbine rotational speed calculating. 16. A method for estimating operating parameter of a gas-turbine aeroengine mounted on an aircraft and having at least a high-pressure turbine rotated by injection of high-pressure gas produced upon ignition and combustion of an air-fuel mixture in a combustion chamber, a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas exiting the high-pressure turbine, a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2), an engine inlet temperature sensor adapted to detect an inlet temperature of the engine (T1), a first bleed off valve position sensor adapted to detect a first amount of bled air flowing through a high-pressure compressor connected to the high-pressure turbine and bled through a first bleed off valve, a second bleed off valve position sensor adapted to detect a second amount of bled air flowing through the high-pressure compressor connected to the high-pressure turbine and bled through a second bleed off valve; comprising the steps of:calculating a corrected rotational speed of the high-pressure turbine (N2K1) corrected by the inlet temperature of the engine (T1) based on the rotational speed of the high-pressure turbine (N2) detected by the high-pressure turbine rotational speed sensor and the inlet temperature of the engine (T1) detected by the engine inlet temperature sensor, and calculating an outlet pressure of the high-pressure compressor (P3) by retrieving preset first characteristics by at least the calculated corrected rotational speed of the high-pressure turbine (N2K1) and the first amount of bled air detected by the first bleed off valve position sensor;calculating a compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving preset second characteristics by at least the second amount of bled air detected by the second bleed off valve position sensor; andcalculating the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the step of compressor outlet pressure calculating and the compensating value (ΔP3) calculated by the step of first compressor outlet pressure compensating value calculating. 17. The method according to claim 16, further including the steps of: calculating a compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving third preset characteristics by at least a flight altitude of the aircraft (ALT); andcalculating the compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving fourth preset characteristics by at least a flight speed of the aircraft (Mn);and the step of final compressor outlet pressure calculating calculates the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the step of compressor outlet pressure calculating and the compensating values (ΔP3) calculated by the steps of first, second and third compressor outlet pressure compensating value calculating. 18. The method according to claim 17, further including the step of: calculating the compensating value (ΔP3) of the outlet pressure of the high-pressure compressor (P3) by retrieving fifth preset characteristics by at least a deviation from an ISA where the aircraft locates (dISA);and the step of final compressor outlet pressure calculating calculates the outlet pressure of the high-pressure compressor (P3) finally based on the outlet pressure of the high-pressure compressor (P3) calculated by the step of compressor outlet pressure calculating and the compensating values (ΔP3) calculated by the steps of first, second, third and fourth compressor outlet pressure compensating value calculating. 19. The method according to claim 16, wherein the step of compressor outlet pressure calculating calculates the outlet pressure of the high-pressure compressor (P3) in terms of a ratio of the outlet pressure of the high-pressure compressor (P3) relative to the inlet pressure of the engine (P1) detected by an engine inlet pressure sensor. 20. The method according to claim 16, further including the step of: discriminating whether or not the compressor outlet pressure sensor is normal by comparing the outlet pressure of the high-pressure compressor (P3) detected by a compressor outlet pressure sensor with the outlet pressure of the high-pressure compressor (P3) calculated by the step of final compressor outlet pressure calculating.
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이 특허에 인용된 특허 (4)
Price, Brian John; Demers, Louis, Controlling a gas turbine engine with a transient load.
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