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1. 发明授权

US06272422B1 Method and apparatus for use in control of clearances in a gas turbine engine 有权
公开(公告)号：US06272422B1
公开(公告)日：2001-08-07
申请号：US09753594
申请日：2001-01-04
申请人： Syed J. Khalid , Craig W. Irwin
发明人： Syed J. Khalid , Craig W. Irwin
IPC分类号： F02C900
摘要： A method and an apparatus for determining the clearance between the rotor blades of a rotor assembly and a shroud disposed radially outside of the rotor assembly is provided that calculates steady-state operating conditions for a given power engine setting and utilizes those steady-state conditions to determine a steady-state clearance at the given power setting. The method and apparatus further calculate instantaneous thermal conditions for the rotor disk, rotor blades, and shroud. The instantaneous thermal conditions are subsequently used to determine the amount of instantaneous thermal expansion of the rotor disk, rotor blades, and shroud. A clearance transient overshoot is determined using the calculated instantaneous thermal expansions. The actual clearance is determined using the steady-state clearance and the clearance transient overshoot.

2. 发明授权

US06231306B1 Control system for preventing compressor stall 有权
标题翻译：防止压缩机失速的控制系统
公开(公告)号：US06231306B1
公开(公告)日：2001-05-15
申请号：US09197864
申请日：1998-11-23
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F02C918
CPC分类号： F04D27/0284 , F01D17/08 , F02C9/18 , F02C9/20 , F05D2270/101
摘要： A control system for preventing a compressor stall in a gas turbine engine includes means for sensing an aerodynamic signal indicative of an impending stall condition. The weak stages of the compressor amplify an upstream disturbance originating in the low pressure compressor or fan, resulting in a discrete frequency disturbance, which is an effective stall precursor. The control system also includes means, responsive to the sensed signal, for processing the signal by isolating the relevant frequencies of the sensed signal, calculating the magnitude of the relevant portions of the sensed signal, comparing the sensed signal to a predetermined threshold indicative of a healthy compressor, and for providing a processed signal indicative of an impending stall condition. The control system further includes means, responsive to the processed signal, for providing an output to initiate corrective action to prevent the impending stall condition. The engine's electronic control system, in response to the output signal, increases the stall margin by either adjusting the compressor variable vanes or modulating the compressor bleed.
摘要翻译：用于防止燃气涡轮发动机中的压缩机失速的控制系统包括用于感测表示即将失速状态的空气动力信号的装置。压缩机的弱阶段放大来自低压压缩机或风扇的上游扰动，导致离散的频率干扰，这是有效的失速前兆。控制系统还包括响应于感测到的信号的装置，通过隔离感测信号的相关频率来处理信号，计算感测信号的相关部分的幅度，将感测到的信号与预定阈值进行比较，健康的压缩机，并且用于提供表示即将发生的失速状态的经处理的信号。控制系统还包括响应于经处理的信号的装置，用于提供输出以启动校正动作以防止即将发生的失速状态。发动机的电子控制系统响应于输出信号，通过调节压缩机可变叶片或调节压缩机流量来增加失速裕度。

3. 发明授权

US6155038A Method and apparatus for use in control and compensation of clearances in a gas turbine 有权
标题翻译：用于控制和补偿燃气轮机间隙的方法和装置
公开(公告)号：US6155038A
公开(公告)日：2000-12-05
申请号：US219912
申请日：1998-12-23
申请人： Craig W. Irwin , Syed J. Khalid
发明人： Craig W. Irwin , Syed J. Khalid
IPC分类号： F01D11/08 , F01D11/24 , F01D25/00 , F02C7/00 , F02C7/28 , F02C9/28 , F02C13/10
CPC分类号： F01D11/24 , F02C9/28
摘要： A method and an apparatus for use with a gas turbine engine receive a signal indicative of an engine operating condition, generate signals representative of thermal conditions of a rotor, blades, and a case, and in response to each of the signals above, determine a signal indicative of a difference between a instantaneous clearance for the thermal conditions and a steady state clearance for the engine operating condition. The determination includes effects related to a temporary difference that results from a difference between the steady state clearance for the engine operating condition and a steady state clearance for a preceding engine operating condition, but does not require computation of the actual temperatures or the steady state temperatures of the rotor, the blades, and the case. A signal indicative of the difference between a instantaneous clearance for the thermal conditions and a steady state clearance for the engine operating condition may be provided to various augmentation schedules.
摘要翻译：一种与燃气涡轮发动机一起使用的方法和装置，接收表示发动机工作状态的信号，产生代表转子，叶片和壳体的热条件的信号，并且响应于上述每个信号，确定一个指示热条件的瞬时间隙与发动机工作状态的稳态间隙之间的差异的信号。该判定包括由于发动机工作状态的稳态间隙与先前的发动机运转状态的稳态间隙之间的差异导致的暂时性差异的影响，但不需要计算实际温度或稳态温度的转子，叶片和壳体。可以向各种增加时间表提供表示热条件的瞬时间隙与发动机工作状态的稳定间隙之间的差异的信号。

4. 发明授权

US5623823A Variable cycle engine with enhanced stability 失效
标题翻译：可变循环发动机具有增强的稳定性
公开(公告)号：US5623823A
公开(公告)日：1997-04-29
申请号：US568039
申请日：1995-12-06
申请人： Steven M. Schirle , Samy Baghdadi , Syed J. Khalid , Gary M. Perkins
发明人： Steven M. Schirle , Samy Baghdadi , Syed J. Khalid , Gary M. Perkins
IPC分类号： F02C9/22 , F02K3/06 , F02K3/075 , F02K3/02
CPC分类号： F02K3/06 , F02K3/075
摘要： A variable cycle gas turbine engine (10) includes a core unit (30) having a guide vane array (36), and a hybrid stage (38) with a rotor blade array (40) and a stator vane array (42). The engine is operable in at least two modes which channel different quantities of working medium air to the core unit, and each mode corresponds to a distinct thermodynamic cycle. The vanes (54) of the hybrid stage stator vane array are bivariable so that the leading segment (140) and trailing segment (146) of each vane are separately adjustable over a range of pitch angles. The bivariable character of the vanes ensures aerodynamic stability of the engine in each of its modes of operation.
摘要翻译：可变循环燃气涡轮发动机（10）包括具有导叶阵列（36）的核心单元（30）和具有转子叶片阵列（40）和定子叶片阵列（42）的混合台（38）。发动机可以以至少两种模式操作，其将不同量的工作介质空气通向核心单元，并且每个模式对应于明显的热力循环。混合级定子叶片阵列的叶片（54）是双变量的，使得每个叶片的前段（140）和后段（146）在桨距角范围内可分别调节。叶片的双重特性确保发动机在其每种操作模式下的气动稳定性。

5. 发明授权

US5357748A Compressor vane control for gas turbine engines 失效
标题翻译：燃气轮机发动机的压缩机叶片控制
公开(公告)号：US5357748A
公开(公告)日：1994-10-25
申请号：US973440
申请日：1992-11-09
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F02C9/54 , F04D27/02 , F02C9/20
CPC分类号： F04D27/0284 , F02C9/54 , F05D2200/211
摘要： In a gas turbine engine a method for thrust variation with reduced compressor RPM excursion is provided in two modes which includes adjusting pivotable compressor vanes mounted upstream of compressor rotor blades, ahead of the conventional vane schedule therefor in a closed loop fashion, responsive to compressor corrected RPM, so as to adjust the fuel demand and engine thrust thereof while maintaining relatively high scheduled compressor corrected RPM scheduled as a function of fan corrected RPM while retaining the conventional method of fuel flow scheduling. Thus mode 1 of the invention adjusts the compressor vanes in advance of the conventional schedule therefor, e.g. pre-closes them on the deceleration side of the Bodie transient and appropriately opens them on the acceleration side of such transient subject to closed loop monitoring of the corrected compressor RPM and being guided thereby so as to result in reduced excursion in such RPM, during both legs of such transient. Because of such reduced RPM excursion, fast changes in engine thrust are possible. In mode 2 of the invention, snap accelerations of a gas turbine engine and its compressor, are assisted by opening the compressor vanes ahead of the conventional schedule therefor in an open loop fashion, not so much for compressor corrected RPM excursion advantage as for improved compressor stall margin. The methods of the invention thus emphasize the primacy of vane control over fuel flow control for reduced compressor RPM excursion in the first mode and increased stall margin in the second mode.
摘要翻译：在燃气涡轮发动机中，具有减小的压缩机RPM偏移的推力变化的方法被提供在两种模式中，其包括调节安装在压缩机转子叶片上游的可枢转的压缩机叶片，在常规叶片计划之前以闭环方式响应于压缩机校正以便调整燃料需求和发动机推力，同时保持作为风扇校正RPM的函数的相对高的预定压缩机校正RPM，同时保持常规的燃料流调度方法。因此，本发明的模式1可以按照常规的日程安排来调节压缩机叶片，例如。在Bodie瞬态的减速侧预先关闭它们，并在这种瞬态的加速侧上适当地打开它们，以对已校正的压缩机RPM进行闭环监测并由其引导，以便在两者期间在这种RPM中导致减小的偏移这种短暂的腿。由于这种减小的RPM偏移，发动机推力的快速变化是可能的。在本发明的模式2中，燃气涡轮发动机及其压缩机的卡扣加速度通过以开环方式打开压缩机叶片，而不是以压缩机校正的RPM偏移优点为前提，以改进压缩机摊位边缘。因此，本发明的方法强调了叶片控制对燃料流量控制的优先性，用于在第一模式中降低的压缩机RPM偏移，并且在第二模式中增加了失速裕度。

6. 发明授权

US5059093A Compressor bleed port 失效
标题翻译：压缩机排气口
公开(公告)号：US5059093A
公开(公告)日：1991-10-22
申请号：US534226
申请日：1990-06-07
申请人： Syed J. Khalid , Brian A. Robideau
发明人： Syed J. Khalid , Brian A. Robideau
IPC分类号： F01D17/10 , F02C9/18 , F04D27/02
CPC分类号： F02C9/18 , F01D17/105 , F04D29/522
摘要： Rectangular bleed ports (24) are circumferentially arranged. Each port has an average radius (r) greater than 30 percent of the port width (W) throughout the reactant surface of the upstream facing edge (30), thereby avoiding flow separation from the surface. A tangent point (36) at the junction of the reactant surface (36) and the inside surface of casing (12) is located a distance (x) upstream to blades (18) greater than 40 percent of the spacing between the blades. This reduces flow losses in the ports caused by blade upwash.
摘要翻译：矩形排出口（24）周向布置。每个端口的平均半径（r）大于在面向上游的边缘（30）的整个反应物表面上的端口宽度（W）的30％，从而避免与表面的流动分离。在反应物表面（36）和壳体（12）的内表面的接合部处的切点（36）位于叶片（18）上游的距离（x），大于叶片间距的40％。这减少了由叶片上洗液引起的端口中的流量损失。

7. 发明授权

US4947643A Active geometry control system for gas turbine engines 失效
标题翻译：燃气轮机发动机主动几何控制系统
公开(公告)号：US4947643A
公开(公告)日：1990-08-14
申请号：US246765
申请日：1988-09-20
申请人： Robert R. Pollak , Syed J. Khalid , Juan A. Marcos
发明人： Robert R. Pollak , Syed J. Khalid , Juan A. Marcos
IPC分类号： F02C9/28 , F02C9/54 , F02K1/16 , F02K1/17
CPC分类号： F02C9/28 , F02C9/54 , F02K1/16 , F02K1/17 , F05D2270/051
摘要： An active control system for use in gas turbine engines synchronizes exhaust nozzle area and burner fuel flow together with pas path variable engine parameters, such as fan variable vane and high compressor variable vane positions. 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.
摘要翻译：用于燃气涡轮发动机的主动控制系统将排气喷嘴区域和燃烧器燃料流与pas路径可变发动机参数（诸如风扇可变叶片和高压缩机可变叶片位置）同步。因此，由于风机和压缩机的转子转速保持较高，所以压缩系统的稳定性极佳，因此可以实现非常快的推力瞬变，从而允许通过气流和燃料直接控制总发动机功率。

8. 发明授权

US4050306A Method and apparatus for measuring pressures 失效
标题翻译：用于测量压力的方法和装置
公开(公告)号：US4050306A
公开(公告)日：1977-09-27
申请号：US661980
申请日：1976-02-27
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： G01L23/00 , F01D21/00 , F02K3/04 , G01L19/00 , G01M15/00 , G01L7/00 , G05D11/00
CPC分类号： G01L19/00 , F01D21/003 , G01M15/00 , Y02T50/671 , Y10T137/2567
摘要： A pair of pressure sensing probe tubes are placed in the fan discharge of a turbofan engine, aft of the outlet guide vanes (OGVs) the tubes being circumferentially spaced by a fraction of the OGV pitch. A comparing means receives both pressures sensed by the double-barrelled probes and aerodynamically actuates to automatically select the higher of the two pressures. An accurate pressure indication representative of the mainstream pressure is therefore obtained despite the localized lower pressure turbulence area that may be caused by the presence of the upstream outlet guide vane(s).
摘要翻译：一对压力感测探针管被放置在涡轮风扇发动机的风扇排放口中，出口导向叶片（OGV）的后部，管周向间隔有一部分OGV间距。比较装置接收由双管探头感测的压力，并且空气动力学地启动以自动选择两个压力中较高者。因此，尽管存在可能由上游出口导流叶片的存在引起的局部较低的压力湍流面积，但仍获得代表主流压力的准确的压力指示。

9. 发明授权

US6164902A Controlling stall margin in a gas turbine engine during acceleration 有权
标题翻译：在加速期间控制燃气轮机的失速余量
公开(公告)号：US6164902A
公开(公告)日：2000-12-26
申请号：US209628
申请日：1998-12-11
申请人： Craig W. Irwin , Syed J. Khalid
发明人： Craig W. Irwin , Syed J. Khalid
IPC分类号： F02C9/00 , F04D27/02 , F01B25/00
CPC分类号： F04D27/02
摘要： A control system for controlling the compressor stall margin during acceleration in a gas turbine engine includes means for sensing signals indicative of the gas flow temperature and gas pressure. The control system further includes signal processing means, responsive to the sensed signals, for synthesizing and providing a processed signal indicative of a measure of compressor destabilization due to heat transfer effects. The control system also includes means, responsive to the processed signal, for providing an output to initiate corrective action to increase compressor stall margin if needed. The engine control means, which is a part of the control system, increases the compressor stall margin by either adjusting the compressor variable vanes, reducing fuel flow or modulating the compressor bleed.
摘要翻译：用于在燃气涡轮发动机加速期间控制压缩机失速余量的控制系统包括用于感测指示气体流动温度和气体压力的信号的装置。控制系统还包括响应于感测到的信号的信号处理装置，用于合成和提供表示由于传热效应引起的压缩机不稳定性的测量的处理信号。控制系统还包括响应于经处理的信号的装置，用于提供输出以启动校正动作，以在需要时增加压缩机失速余量。作为控制系统的一部分的发动机控制装置通过调节压缩机可变叶片，减少燃料流量或调节压缩机流失来增加压缩机失速裕度。

10. 发明授权

US5520508A Compressor endwall treatment 失效
标题翻译：压缩机端壁处理
公开(公告)号：US5520508A
公开(公告)日：1996-05-28
申请号：US350208
申请日：1994-12-05
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F02C7/28 , F01D11/08 , F01D11/12 , F04D27/02 , F01D5/10
CPC分类号： F01D11/127 , F01D11/08 , F04D29/526 , F04D29/685 , Y10S415/914
摘要： The compressor section of an insert gas turbine engine contains a insert installed around the compressor blades that includes cells in a honeycomb configuration. Each cell is inclined at a compound angle to the blade tip to energize the tip air flow as the tip passes over the cell as the blade rotates, improving stall margin with minimum efficiency loss. Each cell is oriented in the direction of the blade chord and faces the advancing blades. As the blade rotates, it sweeps by each cell and high pressure airflow is first captured in the cell from the high pressure side of the blade and released to the low pressure side as the blade passes the cell in the form of a transient energizing jet of high velocity flow in the direction of the airflow across the blade thereby providing effective mixing of the endwall flows and enhancing the tip flow streamwise momentum.
摘要翻译：插入式燃气涡轮发动机的压缩机部分包含安装在包括蜂窝结构的电池的压缩机叶片周围的插入件。当叶片旋转时，每个单元以与叶片尖端的复合角度倾斜以激发尖端空气流，从而以最小的效率损失改善失速余量。每个单元沿着叶片弦的方向定向并面向前进叶片。当叶片旋转时，它被每个单元扫过，并且高压气流首先从叶片的高压侧捕获在单元中，并且当叶片以瞬时通电喷射的形式通过单元时被释放到低压侧在气流穿过叶片的方向上的高速度流动，从而提供端壁流动的有效混合并且增强尖端流动流动动量。

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