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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

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。

3. 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。

4. 发明授权

US5375412A Rotating stall recovery 失效
标题翻译：旋转档位恢复
公开(公告)号：US5375412A
公开(公告)日：1994-12-27
申请号：US51921
申请日：1993-04-26
申请人： Syed J. Khalid , James V. French
发明人： Syed J. Khalid , James V. French
IPC分类号： F02C9/16 , F04D27/02
CPC分类号： F02C9/16 , F04D27/0223 , F04D27/023 , F04D27/0246
摘要： In an aircraft gas turbine engine, stator vane deflection and compressor bleed are controlled to alter the compressor airflow vs. compressor pressure relationship map when stall conditions are detected based on compressor speed and compressor temperature, a change that means that less change in pressure required to nudge the compressor from of a stall, accelerating stall recovery. Once the stall has ceased, the stator deflection and bleed are restored to pre-recovery values.
摘要翻译：在飞机燃气涡轮发动机中，当基于压缩机速度和压缩机温度检测到失速条件时，控制定子叶片偏转和压缩机排放以改变压缩机气流与压缩机压力关系图，这意味着压力变化对于从档位推动压缩机，加速档位恢复。一旦档位停止，定子偏转和流出就恢复到预恢复值。

5. 发明授权

US5165844A On-line stall margin adjustment in a gas turbine engine 失效
标题翻译：燃气涡轮发动机中的在线失速余量调整
公开(公告)号：US5165844A
公开(公告)日：1992-11-24
申请号：US789556
申请日：1991-11-08
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F01D11/20 , F02C9/18 , F04D27/02
CPC分类号： F02C9/18 , F01D11/20 , F04D27/0246
摘要： The deflection angle of a gas turbine stator is adjusted in proportion to the difference between two parameters computed from N.sub.2 and TT2 using the same function generator. One parameter is a reference adjustment under standard conditions for measured N.sub.2 adjusted to sea level and standard temperature. The second parameter is an adjustment for actual altitude conditions. The parameters manifest the clearance between the engine case and the turbine blade tips.
摘要翻译：燃气轮机定子的偏转角度与使用相同函数发生器从N2和TT2计算的两个参数之间的差异成比例地调整。一个参数是在标准条件下对被调节到海平面和标准温度的N2进行参考调整。第二个参数是对实际高度条件的调整。这些参数表明发动机外壳和涡轮叶片尖端之间的间隙。

6. 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。

7. 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。

8. 发明授权

US5269136A Sub-idle stability enhancement and rotating stall recovery 失效
标题翻译：次怠速稳定性增强和旋转失速恢复
公开(公告)号：US5269136A
公开(公告)日：1993-12-14
申请号：US859767
申请日：1992-03-30
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F02K1/17 , F04D27/02 , F02K11/15
CPC分类号： F02K1/17 , F04D27/02
摘要： In an aircraft gas turbine engine having a variable area exhaust, gas turbine compressor operating conditions are sensed to determine a sub-idle condition or a rotating stall. The exhaust area is increased to a maximum when a sub-idle condition is present. If a condition associated with a rotation stall is sensed, fuel flow is decremented but not below a minimum flow. When the rotating stall ends, fuel flow is restored to the normal level and then the engine reaches stabilized operating conditions, the nozzle area is restored at a scheduled rate.
摘要翻译：在具有可变面积排气的飞机燃气涡轮发动机中，检测燃气涡轮压缩机运行状况以确定副空转状态或旋转失速。当存在空闲状态时，排气区域增加到最大值。如果检测到与旋转失速相关联的状况，则燃料流量减少但不低于最小流量。当转动档停止时，燃料流量恢复到正常水平，然后发动机达到稳定的运行状态，喷嘴面积以预定的速度恢复。

9. 发明授权

US5165845A Controlling stall margin in a gas turbine engine during acceleration 失效
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：US5165845A
公开(公告)日：1992-11-24
申请号：US789557
申请日：1991-11-08
申请人： Syed J. Khalid
发明人： Syed J. Khalid
IPC分类号： F01D11/20 , F02C9/18 , F04D27/02
CPC分类号： F02C9/18 , F01D11/20 , F04D27/0246 , F05D2200/11
摘要： Stall margin in a gas turbine compressor is controlled during acceleration by synthesizing the thermal enlargement of critical compressor stages to synthesize the temporary increase in blade-case clearance during acceleration. The change in clearance is used to produce an augmenting stator vane deflection signal which is summed with a steady state vane deflection signal to increase deflection during acceleration until the clearance returns to a nominal level when the expansion of the compressor parts stabilize.
摘要翻译：在加速期间通过合成关键压缩机级的热膨胀来合成在加速期间刀片间隙的临时增加来控制燃气轮机压缩机中的失速边界。间隙的变化被用于产生增大的定子叶片偏转信号，其与稳态叶片偏转信号相加，以在加速期间增加偏转，直到当压缩机部件的膨胀稳定时，间隙返回到标称水平。

10. 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。

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