-
公开(公告)号：EP0185600A1
公开(公告)日：1986-06-25
申请号：EP85630177.5
申请日：1985-10-31
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2270/02 , F05D2270/023
摘要： By utilizing compensating parameters required for steady state operation of a gas turbine engine which processed variables of compressor speed, compressor pressure and altitude a derivative of the variable desired is synthesized and compared to the actual value in a closed- loop system for limiting the rate of change of fuel flow in an engine treatment condition. In a twin spool engine a function generator responding to speed for the low pressure compressor and altitude generates a signal indicative of rate of change if the speed of the high pressure compressor. The signal is compensated for time constants consistant with the dynamics of the engine and compared with a compensated actual high pressure compressor speed. The error produced with a gain generated from corrected high pressure compressor speed inputs the main electronic digital fuel control. (Fig. 1)
-
公开(公告)号：EP0187115B1
公开(公告)日：1992-08-12
申请号：EP85630228.6
申请日：1985-12-18
-
公开(公告)号：EP0187114B1
公开(公告)日：1990-06-20
申请号：EP85630179.1
申请日：1985-10-31
CPC分类号： F02C9/18 , F04D27/0223 , F04D27/023 , F05D2200/11
-
公开(公告)号：EP0185601A2
公开(公告)日：1986-06-25
申请号：EP85630178.3
申请日：1985-10-31
CPC分类号： G01P5/00 , F04D27/0284
摘要： The cessation of stall/surge in the compressor of a twin spool gas turbine engine is detected by comparing by digital electronics and engines sensed burner pressure with a burner pressure calculated from corrected low pressure compressor speed and sensed airplane Mach number which has been compensated to approximate engine dynamics. (Fig. 3)
-
公开(公告)号：EP0187115A3
公开(公告)日：1988-08-17
申请号：EP85630228
申请日：1985-12-18
摘要： @ A control system for a twin spool gas turbine engine for synthesizing a control parameter for the engine (such as the ratio of high compressor inlet temperature to low compressor inlet temperature) includes a function generator responsive to an engine operating parameter (such as corrected rotor speed) to generate a simulated value of the control parameter for a base engine configuration. A second function generator, responsive to an engine operating parameter, generates a simulated value of the difference between the value of the control parameter for the base engine configuration and the value of the parameter for another configuration. This difference is operated upon to correct it to the actual engine configuration. The corrected difference is added to the simulated value of the control parameter for the base configuration to give a simulated value of the control parameter for the actual engine configuration.
-
公开(公告)号：EP0187114A2
公开(公告)日：1986-07-09
申请号：EP85630179.1
申请日：1985-10-31
CPC分类号： F02C9/18 , F04D27/0223 , F04D27/023 , F05D2200/11
摘要： Flexibility in the control of the compressor bleed valve is of the type utilized in a twin spool axial flow engine for preventing compressor surge is manifested by electronically summing an approximated burner pressure that has a first order time constant introduced to actual burner pressure and a burner pressure limit that is scheduled as a function of corrected high pressure compressor speed and the altitude of the aircraft. The signal may be treated by a hysteresis circuit to stabilize the bleed valve.
-
公开(公告)号：EP0185601B1
公开(公告)日：1990-06-20
申请号：EP85630178.3
申请日：1985-10-31
CPC分类号： G01P5/00 , F04D27/0284
-
公开(公告)号：EP0185600B1
公开(公告)日：1989-06-14
申请号：EP85630177.5
申请日：1985-10-31
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2270/02 , F05D2270/023
-
公开(公告)号：EP0187114A3
公开(公告)日：1987-05-06
申请号：EP85630179
申请日：1985-10-31
CPC分类号： F02C9/18 , F04D27/0223 , F04D27/023 , F05D2200/11
摘要： Flexibility in the control of the compressor bleed valve is of the type utilized in a twin spool axial flow engine for preventing compressor surge is manifested by electronically summing an approximated burner pressure that has a first order time constant introduced to actual burner pressure and a burner pressure limit that is scheduled as a function of corrected high pressure compressor speed and the altitude of the aircraft. The signal may be treated by a hysteresis circuit to stabilize the bleed valve.
-
公开(公告)号：EP0185601A3
公开(公告)日：1987-05-06
申请号：EP85630178
申请日：1985-10-31
CPC分类号： G01P5/00 , F04D27/0284
摘要： The cessation of stall/surge in the compressor of a twin spool gas turbine engine is detected by comparing by digital electronics and engines sensed burner pressure with a burner pressure calculated from corrected low pressure compressor speed and sensed airplane Mach number which has been compensated to approximate engine dynamics. (Fig. 3)
-
-
-
-
-
-
-
-
-
搜索结果
11 条记录 (耗时 0.009 秒)
