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公开(公告)号：WO2014099071A2
公开(公告)日：2014-06-26
申请号：PCT/US2013061632
申请日：2013-09-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MEISNER RICHARD P , WINEBRENNER BRIAN V , FEULNER MATTHEW R , KARPMAN BORIS , MARCOS JUAN A , MA DAVID L
CPC classification number: F01D17/00 , F01D17/08 , F02C9/18 , F02C9/52 , F02C9/54 , F04D27/001 , F05D2270/101
Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.
Abstract translation: 燃气涡轮发动机包括压缩机，燃烧器，涡轮机和电子发动机控制系统。 压缩机，燃烧器和涡轮机以流动系列布置。 电子发动机控制系统被配置为从发动机模型生成压缩机失速余量的实时估计，以及指令发动机执行器，以校正压缩机失速余量的实时估计与所需失速余量之间的差异。
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公开(公告)号：DE68928159D1
公开(公告)日：1997-08-14
申请号：DE68928159
申请日：1989-09-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： POLLAK ROBERT R , MARCOS JUAN A , KHALID SYED J
Abstract: An active control system for use in gas turbine engines synchronizes exhaust nozzle (26) area and burner fuel flow together with gas path variable engine parameters, such as fan variable vane and high compressor variable vane positions (36, 38, 40). As a result, extremely fast thrust transients are possible with optimized compression system stability, since fan and compressor rotor speeds are held high, allowing total engine power to be controlled by air flow and fuel flows directly. Time responsiveness to thrust demands for a fan jet engine of the type that includes twin spools and a variable inlet at the fan is enhanced by regulating air flow through the variable inlet while holding low pressure compressor speed constant. The thrust change is targeted as a function of power lever position which generates a low pressure compressor parametric as a function of engine and aircraft operating variables. This parameter is then utilized to control both the inlet variable vanes and fuel flow to 1) attain the targeted value and 2) return the engine to its steady state operating line after a given time interval. The time responsiveness and engine stability for acceleration and deceleration engine transient is enhanced by control mechanism that synchronously adjusts fuel flow and high pressure compressor vane position as a function of corrected low pressure compressor speed in a twin spool axial flow turbine power plant. The acceleration and deceleration mode is targeted by power lever position and the target is attained by adjusting the vane position at a constant high pressure compressor speed and returned to a fuel efficient and engine stable steady state operating line by concomittantly adjusting fuel flow and vane position.
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公开(公告)号：DE68928159T2
公开(公告)日：1997-10-30
申请号：DE68928159
申请日：1989-09-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： POLLAK ROBERT R , MARCOS JUAN A , KHALID SYED J
Abstract: An active control system for use in gas turbine engines synchronizes exhaust nozzle (26) area and burner fuel flow together with gas path variable engine parameters, such as fan variable vane and high compressor variable vane positions (36, 38, 40). As a result, extremely fast thrust transients are possible with optimized compression system stability, since fan and compressor rotor speeds are held high, allowing total engine power to be controlled by air flow and fuel flows directly. Time responsiveness to thrust demands for a fan jet engine of the type that includes twin spools and a variable inlet at the fan is enhanced by regulating air flow through the variable inlet while holding low pressure compressor speed constant. The thrust change is targeted as a function of power lever position which generates a low pressure compressor parametric as a function of engine and aircraft operating variables. This parameter is then utilized to control both the inlet variable vanes and fuel flow to 1) attain the targeted value and 2) return the engine to its steady state operating line after a given time interval. The time responsiveness and engine stability for acceleration and deceleration engine transient is enhanced by control mechanism that synchronously adjusts fuel flow and high pressure compressor vane position as a function of corrected low pressure compressor speed in a twin spool axial flow turbine power plant. The acceleration and deceleration mode is targeted by power lever position and the target is attained by adjusting the vane position at a constant high pressure compressor speed and returned to a fuel efficient and engine stable steady state operating line by concomittantly adjusting fuel flow and vane position.
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公开(公告)号：EP2900986A4
公开(公告)日：2016-08-03
申请号：EP13864686
申请日：2013-09-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MEISNER RICHARD P , WINEBRENNER BRIAN V , FEULNER MATTHEW R , KARPMAN BORIS , MARCOS JUAN A , MA DAVID L
CPC classification number: F01D17/00 , F01D17/08 , F02C9/18 , F02C9/52 , F02C9/54 , F04D27/001 , F05D2270/101
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