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公开(公告)号：DE69200406D1
公开(公告)日：1994-10-20
申请号：DE69200406
申请日：1992-03-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BRUUN EUGENE ROBERT , KOS JOSEPH MICHAEL
Abstract: A gas turbine engine bleed air system (10) in which air flow from a high pressure (HP) and a low pressure (LP) compressor stage of a gas turbine engine are mixed together, by controlling the pressure at the outlet of a proportional valve, (PRV) the pressure is controlled by modulating the flow area of the proportional valve (HPSOV) through which the high pressure air flows in order to achieve a scheduled pressure value, where the scheduled pressure value is determined as a function of a temperature error at a location downstream of the proportional valve (PRV) in the bleed air system.
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公开(公告)号：DE69201452D1
公开(公告)日：1995-03-30
申请号：DE69201452
申请日：1992-03-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BRUUN EUGENE ROBERT
Abstract: Bleed air flow from each engine of a multi-engine gas turbine powered aircraft is determined by using venturi flow probe sensors (50,100) which each include a venturi (52,102). The pressure differential associated with the pressure within the throat of the venturis (52,102) and the pressure immediately upstream of the venturi is partially indicative of the bleed air flow associated with the respective engine. The appropriate sensed pressure and temperature values are provided to a controller (18) which calculates the bleed air flow from each engine. The controller (18) also calculates a trim signal (224) which is used to partially control the position of pressure regulating valves (14,64) in order to substantially equalize the flow of bleed air from each of the gas turbine engines.
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公开(公告)号：DE69201452T2
公开(公告)日：1995-06-14
申请号：DE69201452
申请日：1992-03-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BRUUN EUGENE ROBERT
Abstract: Bleed air flow from each engine of a multi-engine gas turbine powered aircraft is determined by using venturi flow probe sensors (50,100) which each include a venturi (52,102). The pressure differential associated with the pressure within the throat of the venturis (52,102) and the pressure immediately upstream of the venturi is partially indicative of the bleed air flow associated with the respective engine. The appropriate sensed pressure and temperature values are provided to a controller (18) which calculates the bleed air flow from each engine. The controller (18) also calculates a trim signal (224) which is used to partially control the position of pressure regulating valves (14,64) in order to substantially equalize the flow of bleed air from each of the gas turbine engines.
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公开(公告)号：DE69200406T2
公开(公告)日：1995-02-16
申请号：DE69200406
申请日：1992-03-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BRUUN EUGENE ROBERT , KOS JOSEPH MICHAEL
Abstract: A gas turbine engine bleed air system (10) in which air flow from a high pressure (HP) and a low pressure (LP) compressor stage of a gas turbine engine are mixed together, by controlling the pressure at the outlet of a proportional valve, (PRV) the pressure is controlled by modulating the flow area of the proportional valve (HPSOV) through which the high pressure air flows in order to achieve a scheduled pressure value, where the scheduled pressure value is determined as a function of a temperature error at a location downstream of the proportional valve (PRV) in the bleed air system.
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