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1. 发明授权

US4928240A Active clearance control 失效
标题翻译：主动间隙控制
公开(公告)号：US4928240A
公开(公告)日：1990-05-22
申请号：US160052
申请日：1988-02-24
申请人： Samuel H. Davison , Kevin H. Kast , Aidan W. Clark
发明人： Samuel H. Davison , Kevin H. Kast , Aidan W. Clark
IPC分类号： F01D11/10 , F01D11/08 , F01D11/24 , F02C7/28 , G01B21/16
CPC分类号： F01D11/24
摘要： The invention relates to a control system which controls the diameter of a turbine shroud which surrounds a turbine in a gas turbine aircraft engine. The invention seeks to minimize the clearance between the turbine rotor and the shroud. Air is bled from the compressor in the engine and ducted to the shroud in order to heat or cool the shroud in order to, respectively, either expand or shrink the shroud to a proper diameter. The air temperature which is required is computed based on compressor speed and other engine parameters, but not upon directly measured rotor temperature, despite the fact that rotor temperature has a significant influence upon rotor diameter, and thus upon shroud diameter needed. Air at two different temperatures is bled from two different compressor stages in the engine and mixed together in a ratio which is determined according to flight conditions, in order to provide air of the required temperature for the shroud, and then ducted to the shroud in order to modify shroud size. Further, during accelerations and decelerations of the engine, a different air temperature is provided, as compared with that provided during steady state operation. In the event that the system just described should fail, back-up systems control shroud diameter. There exist two back-up systems, one for use during steady state, and the other for use during accelerations and decelerations.

2. 发明授权

US5187936A Continuous flow fuel circulation system 失效
标题翻译：连续流量燃料循环系统
公开(公告)号：US5187936A
公开(公告)日：1993-02-23
申请号：US599171
申请日：1990-10-17
申请人： Kevin H. Kast , William J. Myers, Jr.
发明人： Kevin H. Kast , William J. Myers, Jr.
IPC分类号： F02C7/22 , F02C7/228 , F02C7/232 , F02C9/28 , F02K3/10
CPC分类号： F02C7/232 , F05D2260/602
摘要： An improved augmentor fuel supply system including a fuel source, a pump for pressurizing the fuel, a flow control means for controlling the flow and pressure of fuel to a fuel disbursement means (e.g., an augmentor) and a return path for recirculating unburned fuel. The flow control means includes a restrictor means such as a small orifice in parallel with a controllable valve. The restrictor means allows fuel to flow to the fuel disbursement means when the controllable valve is shut off. Further, according to the present invention, a second restrictor means, such as a small orifice is included in the return path. Finally, a check valve is included in the return path to ensure that fuel does not flow into the augmentor through the return path.

3. 发明授权

US5148671A Fuel circulation control system 失效
标题翻译：燃油循环控制系统
公开(公告)号：US5148671A
公开(公告)日：1992-09-22
申请号：US599211
申请日：1990-10-17
申请人： Kevin H. Kast , William J. Myers, Jr.
发明人： Kevin H. Kast , William J. Myers, Jr.
IPC分类号： F02C7/22 , F02C7/228 , F02C9/28 , F02K3/10 , F23K5/04 , F23N1/00 , F23N5/18
CPC分类号： F23K5/04 , F23N1/002 , F23N5/184 , F23N2023/00
摘要： A control circuit adapted to receive at least first, second and third input signals. The first input signal is a signal representative of the fuel pressure at the output of a pump. The second signal is a signal representative of the fuel pressure in the manifold of fuel disbursement means which is supplied through a controllable valve, by the fuel pump. The third signal is a signal representative of the pressure at the inlet to the pump. The control circuit further includes a feedback path for continuously circulating fuel from the manifold to the pump inlet. In one arrangement of the fuel supply system, there is an aperture in parallel with the controllable valve and an aperture in the feedback path.

4. 发明授权

US5341635A Fuel circulation control method 失效
标题翻译：燃油循环控制方法
公开(公告)号：US5341635A
公开(公告)日：1994-08-30
申请号：US855972
申请日：1992-03-23
申请人： Kevin H. Kast , William J. Myers, Jr.
发明人： Kevin H. Kast , William J. Myers, Jr.
IPC分类号： F02C7/22 , F02C7/228 , F02C9/28 , F02K3/10 , F23K5/04 , F23N1/00 , F23N5/18
CPC分类号： F23K5/04 , F23N1/002 , F23N5/184 , F23N2023/00
摘要： A control circuit adapted to receive at least first, second and third input signals. The first input signal is a signal representative of the fuel pressure at the output of a pump. The second signal is a signal representative of the fuel pressure in the manifold of fuel disbursement means which is supplied through a controllable valve, by the fuel pump. The third signal is a signal representative of the pressure at the inlet to the pump. The control circuit further includes a feedback path for continuously circulating fuel from the manifold to the pump inlet. In one arrangement of the fuel supply system, there is an aperture in parallel with the controllable valve and an aperture in the feedback path.
摘要翻译：一种适于接收至少第一，第二和第三输入信号的控制电路。第一输入信号是代表泵的输出处的燃料压力的信号。第二信号是表示通过燃料泵通过可控阀提供的燃料支出装置的歧管中的燃料压力的信号。第三个信号是代表泵入口处的压力的信号。控制电路还包括用于将燃料从歧管连续循环到泵入口的反馈路径。在燃料供应系统的一种布置中，存在与可控阀平行的孔和反馈路径中的孔。

5. 发明授权

US5752674A Sensor ice shield 失效
标题翻译：传感器冰盾
公开(公告)号：US5752674A
公开(公告)日：1998-05-19
申请号：US700955
申请日：1996-08-21
申请人： John S. Mears , Ronald A. Bulow , David L. Joyce , Kevin H. Kast
发明人： John S. Mears , Ronald A. Bulow , David L. Joyce , Kevin H. Kast
IPC分类号： G01D21/02 , B64D15/16 , F01D25/02 , F02C7/00 , F02C7/047 , F02C7/055 , B64D15/00
CPC分类号： F01D25/02 , B64D15/16 , F02C7/047 , Y02T50/671
摘要： A system is provided for reducing ice mass on an aircraft engine. A compressor inlet temperature and pressure sensor measures total temperature and total pressure at the inlet to the engine compressor. An ice shield is provided, wherein a plurality of wedge portions has multiple protrusions for promoting ice formation in multiple locations. The ice shield is separable from the sensor with which it interfaces. The ice shield comprises straight angle wedge shapes and curved surfaces to separate and minimize ice accretion in desired locations. The mass of each resultant ice formation is reduced to a size that the compressor inlet blades can withstand without deformation.
摘要翻译：提供了一种用于减少飞机发动机上的冰块的系统。压缩机入口温度和压力传感器测量发动机压缩机入口处的总温度和总压力。提供了一种防冰罩，其中多个楔形部分具有多个用于促进多个位置处的冰的突起。冰盾与传感器分离，与之接触。冰盾包括直角楔形和弯曲表面，以分离和最小化所需位置的积冰。每个所得冰层的质量减小到压缩机入口叶片能够承受而不变形的尺寸。

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