Aircraft engine management for fuel conservation method
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-007/70
G01S-003/02
F02C-006/00
G01C-023/00
출원번호
US-0226335
(2011-09-06)
등록번호
US-8401719
(2013-03-19)
발명자
/ 주소
Wick, Hal Gerard
출원인 / 주소
Wick, Hal Gerard
대리인 / 주소
Lemaire, Charles A.
인용정보
피인용 횟수 :
0인용 특허 :
18
초록
A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent.
대표청구항▼
1. A computerized method for reducing a net amount of fuel consumed during a flight when running a jet engine on an airplane, wherein the jet engine includes a housing having an inlet end and an outlet end, and a compressor located between the inlet end and the outlet end, and wherein the airplane i
1. A computerized method for reducing a net amount of fuel consumed during a flight when running a jet engine on an airplane, wherein the jet engine includes a housing having an inlet end and an outlet end, and a compressor located between the inlet end and the outlet end, and wherein the airplane includes an engine-control computer for controlling the engine, the method comprising: measuring a first pressure near the inlet end of the jet engine;measuring a second pressure near the outlet end of the jet engine; andcontrolling a speed of the compressor with the engine-control computer to maintain a value of the second pressure divided by the first pressure at a controlled first value in a range of 0.9 to 1.15 at a plurality of descent altitudes from cruising altitude to approximately 9,000-11,000 feet at which the jet engine, if set to idle, would have a value of the second pressure divided by the first pressure of less than the first value in order to reduce the jet engine acting as a speed brake for the airplane during a descent of the airplane, in order to reduce the net amount of fuel consumed during the flight. 2. The method of claim 1, wherein the controlling of the compressor speed further includes maintaining the value of the second pressure divided by the first pressure in a range of 0.90 to 1.10 during the descent of the airplane. 3. The method of claim 1, wherein the controlling of the compressor speed further includes maintaining the value of the second pressure divided by the first pressure in a range of 0.95 to 1.05 during the descent of the airplane. 4. The method of claim 1, wherein the controlling of the compressor speed further includes maintaining the value of the second pressure divided by the first pressure in a range of 0.98 to 1.02 during the descent of the airplane. 5. The method of claim 1, wherein the controlling of the compressor speed further includes maintaining the value of the second pressure divided by the first pressure in a range of 0.99 to 1.01 during the descent of the airplane. 6. The method of claim 1, wherein the controlling of the compressor speed further includes maintaining the value of the second pressure divided by the first pressure substantially at 1.0 during the descent of the airplane. 7. The method of claim 1, wherein the measuring of the second pressure further includes measuring the second pressure near an end of a nozzle portion of the housing, and wherein the measuring of the first pressure further includes measuring the first pressure near a front face of the compressor. 8. A computerized method for reducing a net amount of fuel consumed during a flight when controlling engine speed of a jet engine of an aircraft during a descent of the aircraft, wherein the aircraft includes an engine-control computer for controlling the engine, the method comprising: measuring engine pressure near a front of the jet engine;measuring the engine pressure near a rear of the jet engine;determining an engine-pressure ratio (EPR) by dividing the engine pressure near the rear of the jet engine by the engine pressure near the front of the jet engine; andcontrolling the engine speed with the engine-control computer to maintain the engine-pressure ratio at a controlled first EPR value in a range of 0.9 to 1.1 at a plurality of descent altitudes from cruising altitude to approximately 9,000-11,000 feet at which the jet engine, if set to idle, would have an engine-pressure ratio of less than the first EPR value in order to reduce the jet engine acting as a speed brake for the aircraft during the descent of the aircraft, in order to reduce the net amount of fuel consumed during the flight. 9. The method of claim 8, wherein the controlling of the engine speed further includes controlling the engine speed to maintain the engine-pressure ratio in a range of 0.95 to 1.05 during the descent of the aircraft. 10. The method of claim 8, wherein the controlling of the engine speed further includes controlling the engine speed to maintain the engine-pressure ratio in a range of 0.98 to 1.02. 11. The method of claim 8, wherein the controlling of the engine speed further includes controlling the engine speed to maintain the engine-pressure ratio in a range of 0.99 to 1.01. 12. The method of claim 8, wherein the controlling of the engine speed further includes controlling the engine speed to maintain the engine-pressure ratio substantially at 1.0. 13. A computerized method for reducing a net amount of fuel consumed during a flight when running a jet engine on an airplane, the jet engine including a speed-control module, the method comprising: determining an engine pressure ratio (EPR) by dividing a first engine pressure near a rear of the jet engine by a second engine pressure near a front of the jet engine; andcontrolling an engine speed of the jet engine with the speed-control module during a descent of the airplane to maintain the engine-pressure ratio at a controlled first EPR value in a range between 0.9 and 1.15 at a plurality of descent altitudes from cruising altitude to approximately 9,000-11,000 feet at which the jet engine, if set to idle, would have an engine-pressure ratio of less than the first EPR value in order to reduce the jet engine acting as a speed brake for the airplane during the descent of the airplane, in order to reduce the net amount of fuel consumed during the flight. 14. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio in a range between 0.9 and 1.10 during the descent. 15. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio in a range between 0.95 and 1.05 during the descent. 16. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio in a range between 0.98 and 1.02 during the descent. 17. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio in a range between 0.99 and 1.01 during the descent. 18. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio substantially at 1.0. 19. The method of claim 13, wherein the controlling of the engine speed further includes controlling a rotational speed of a compressor of the jet engine. 20. The method of claim 13, wherein the controlling of the engine speed further includes maintaining the engine-pressure ratio in a range between 1.0 and 1.05 during the descent.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (18)
Schmidt-Roedenbeck Heiner (berlingen DEX) Wst Peter (berlingen DEX) Wellern Wilfried (Uhldingen-Mhlhofen DEX), Apparatus for controlling the rotary speed in turbo-jet engines for aircraft.
Russ ; deceased Daniel G. (late of Fort Wayne IN by Ruth S. Russ ; executrix) Bertsche George J. (Woodburn IN), Method and apparatus for maximizing fuel efficiency for jet engines.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.