公开(公告)号：US5752378A

公开(公告)日：1998-05-19

申请号：US683107

申请日：1996-07-16

Applicant: Saul Mirsky ,  Naum Staroselsky ,  Brett W. Batson ,  Krishnan Narayanan

Inventor： Saul Mirsky ,  Naum Staroselsky ,  Brett W. Batson ,  Krishnan Narayanan

IPC: F02C9/28 ,  F04D27/02

CPC classification number: F02C9/28 ,  F04D27/02 ,  F05D2270/101

Abstract: An improved method is provided for controlling fuel flow to the combustor of a gas generator turbine during sudden changes in load or during a surge cycle of the process turbocompressor. Surge control is initiated by analog input signals emanating from various devices located throughout the compressor-process system. The fuel control system includes input signals from the gas turbine driver. These signals are acted upon by the fuel control system which transmits a signal to a fuel valve actuator that controls the valve that meters fuel to the combustor. In addition to this sequence of control communication, however, is a rate-of-change in the amount of the fuel provided. The rate of the increase of the amount of fuel is determined by current operating functions of the fuel control system. However, because of the characteristics of general load rejection and recovery, and the abrupt nature of surge, the rate of change in the flow rate of fuel is extremely high. This rapid increase of fuel to the combustor may lead to dangerous excursions in temperature, resulting in high temperatures in gas turbine elements. Consequently, a new function is added to the fuel control system's operation whereby improved regulation of the rate of increase of fuel is achieved. This new function receives a signal that either surge or a change in load has been detected. Next, a signal is transmitted to the fuel valve actuator, regulating fuel to the combustor, thus power to the power turbine, thereby preventing overspeeding. After that, the rate of change of the fuel valve is limited for a period of time. Once recovery has been accomplished, the change rate of the fuel valve is gradually returned to a normal operating setting.

Abstract translation: 提供了一种改进的方法来控制在负载突然变化期间或在处理涡轮压缩机的喘振周期期间向燃气发电机涡轮机的燃烧器流动。 浪涌控制由位于整个压缩机过程系统的各种设备发出的模拟输入信号启动。 燃料控制系统包括来自燃气涡轮驱动器的输入信号。 这些信号由燃料控制系统起作用，该燃料控制系统将信号发送到燃料阀致动器，燃料阀致动器控制将燃料喷射到燃烧器的阀。 然而，除了这个控制通信序列之外，还提供了所提供的燃料的量的变化率。 燃料量的增加率由燃油控制系统的当前运行功能决定。 然而，由于一般的负载抑制和回复特性以及浪涌的突然特性，燃料流量的变化率非常高。 燃料对燃烧器的快速增加可能导致温度的危险偏移，导致燃气轮机元件的高温。 因此，在燃料控制系统的操作中增加了新的功能，从而实现了对燃料增加速率的改进的调节。 该新功能接收到已检测到浪涌或负载变化的信号。 接下来，信号被传送到燃料阀致动器，调节到燃烧器的燃料，从而对动力涡轮机供电，从而防止超速。 之后，燃料阀的变化率被限制一段时间。 一旦恢复完成，燃料阀的变化率逐渐恢复到正常的运行状态。

公开(公告)号：US5743715A

公开(公告)日：1998-04-28

申请号：US546114

申请日：1995-10-20

Applicant: Serge Staroselsky ,  Brett W. Batson ,  Saul Mirsky ,  Vadim Shapiro

Inventor： Serge Staroselsky ,  Brett W. Batson ,  Saul Mirsky ,  Vadim Shapiro

IPC: F04D15/00 ,  F04D27/00 ,  F04D27/02 ,  F04B41/06 ,  F04B49/00

CPC classification number: F04D27/0269 ,  F04D27/02

Abstract: Balancing the load between compressors is not trivial. An approach is disclosed to balance loads for compression systems which have the characteristic that the surge parameters, S, change in the same direction with rotational speed during the balancing process. Load balancing control involves equalizing the pressure ratio, rotational speed, or power (or functions of these) when the compressors are operating far from surge. Then, as surge is approached, all compressors are controlled, such that they arrive at their surge control lines simultaneously.

Abstract translation: 平衡压缩机之间的负载并不是微不足道的。 公开了一种用于平衡压缩系统的负载的方法，其特征在于浪涌参数S在平衡过程期间以相同方向与转速相同地改变。 负载平衡控制包括当压缩机远离浪涌运行时平衡压力比，转速或功率（或这些功能）。 然后，随着浪涌的进行，所有的压缩机被控制，使得它们同时到达它们的喘振控制线。

公开(公告)号：US5508943A

公开(公告)日：1996-04-16

申请号：US225448

申请日：1994-04-07

Applicant: Brett W. Batson ,  Krishnan Narayanan

Inventor： Brett W. Batson ,  Krishnan Narayanan

IPC: F04D27/02 ,  F04D17/14

CPC classification number: F04D27/0207

Abstract: A method and apparatus are disclosed for protecting turbocompressors from unstable flow conditions (surge and stall). To accomplish this, it is necessary to easily and accurately calculate a compressor's operating point and its distance from the interface between the surge region and the stable region--this interface is referred to as the Surge Limit Interface. The proximity of the operating point to the Surge Limit Interface is calculated using measurements of properties throughout the compressor-process system. It is crucial that the calculation be invariant to suction conditions, especially gas composition. Disclosed are three coordinates, T.sub.r (reduced torque), P.sub.r (reduced power), and N.sub.e (equivalent speed). Each of these can be combined with other invariant parameters to construct coordinate systems in which to define the Surge Limit Interface and measure the distance of the operating point to that interface.

Abstract translation: 公开了一种用于保护涡轮压缩机免受不稳定流动条件（浪涌和失速）的方法和装置。 为了实现这一点，有必要轻松而准确地计算出压缩机的工作点及其与浪涌区域和稳定区域之间的接口的距离 - 该接口被称为浪涌限制接口。 通过整个压缩机过程系统的性能测量，计算工作点与浪涌限制界面的接近度。 重要的是，计算对于吸入条件，特别是气体组成是不变的。 公开了Tr（降低转矩），Pr（降低功率）和Ne（等效速度）三个坐标。 它们中的每一个可以与其他不变参数组合以构造坐标系，其中定义浪涌极限接口并测量操作点与该接口的距离。

公开(公告)号：US5908462A

公开(公告)日：1999-06-01

申请号：US761124

申请日：1996-12-06

Applicant: Brett W. Batson

Inventor： Brett W. Batson

IPC: F04D27/02 ,  G06G7/70 ,  F04B49/00

CPC classification number: F04D27/0207

Abstract: A turbocompressor's Surge Limit Line, displayed in coordinates of reduced flow rate (q.sub.r) and reduced head (h.sub.r), can be difficult to characterize if the slope of the line is small; that is, nearly horizontal. And it can be especially difficult to characterize if the surge line exhibits a local maximum or minimum, or both. This is often the case with axial compressors having adjustable inlet guide vanes, and for centrifugal compressors with variable inlet guide vanes and diffuser vanes. With their prime objective being the prevention of surge-induced compressor damage and process upsets, antisurge control algorithms should compensate for variations in suction conditions by calculating both the operating point and the Surge Limit Line, utilizing specific (invariant) coordinates derived by using the notations of similitude or dimensional analysis. The result is that the surge limit is invariant (stationary) to suction conditions. This disclosure describes a new method of antisurge control for turbocompressors, which uses combinations of invariant coordinates that differ from those revealed in the prior art. Subsequently, the key to this invention is that any combination (linear or nonlinear) of invariant coordinates is also invariant.

Abstract translation: 如果线路的斜率较小，则可能难以表征涡轮压缩机的减小流量（qr）和减小的头（hr）坐标的浪涌限制线; 也就是说，几乎是水平的。 如果浪涌线显示局部最大值或最小值，或两者兼而有之，则特别难以表征。 对于具有可调进口导向叶片的轴向压缩机和具有可变入口导向叶片和扩散器叶片的离心式压缩机，通常是这种情况。 它的主要目标是防止浪涌引起的压缩机损坏和过程失调，防喘振控制算法应通过计算工作点和浪涌极限线来补偿吸入条件的变化，利用通过使用符号得到的特定（不变量）坐标 的相似或尺寸分析。 结果是浪涌极限是吸入条件不变的（静止的）。 本公开描述了涡轮压缩机的防喘振控制的新方法，其使用与现有技术中揭示的那些不同的不变坐标的组合。 随后，本发明的关键是不变坐标的任何组合（线性或非线性）也是不变的。

公开(公告)号：US5879133A

公开(公告)日：1999-03-09

申请号：US844606

申请日：1997-04-21

Applicant: Saul Mirsky ,  Naum Staroselsky ,  Brett W. Batson ,  Krishnan Narayanan

Inventor： Saul Mirsky ,  Naum Staroselsky ,  Brett W. Batson ,  Krishnan Narayanan

IPC: F02C9/28 ,  F04D27/02 ,  F04B49/20

CPC classification number: F02C9/28 ,  F04D27/02 ,  F05D2270/101

Abstract: A method is provided for controlling fuel flow to the combustor of a gas generator turbine during sudden changes in load or during a surge cycle of the process turbocompressor. Surge control is initiated by analog input signals emanating from various devices located throughout the compressor-process system. The fuel control system includes input signals from the gas turbine driver. These signals are acted upon by the fuel control system which transmits a signal to a fuel valve actuator that controls the valve that meters fuel to the combustor. In addition to this sequence of control communication, however, is a rate-of-change in the amount of the fuel provided. The rate of the increase of the amount of fuel is determined by current operating functions of the fuel control system. However, because of the characteristics of general load rejection and recovery, and the abrupt nature of surge, the rate of change in the flow rate of fuel is extremely high. This rapid increase of fuel to the combustor may lead to dangerous excursions in temperature, resulting in high temperatures in gas turbine elements. Consequently, a new function is added to the fuel control system's operation whereby improved regulation of the rate of increase of fuel is achieved. This new function receives a signal that either surge or a change in load has been detected. Next, a signal is transmitted to the fuel valve actuator, regulating fuel to the combustor, thus power to the power turbine, thereby preventing overspeeding. After that, the rate of change of the fuel valve is limited for a period of time. Once recovery has been accomplished, the change rate of the fuel valve is gradually returned to a normal operating setting.

Abstract translation: 提供了一种用于控制在负载突然变化或过程涡轮压缩机的喘振周期期间向燃气发电机涡轮机的燃烧器流动的燃料。 浪涌控制由位于整个压缩机过程系统的各种设备发出的模拟输入信号启动。 燃料控制系统包括来自燃气涡轮驱动器的输入信号。 这些信号由燃料控制系统起作用，该燃料控制系统将信号发送到燃料阀致动器，燃料阀致动器控制将燃料喷射到燃烧器的阀。 然而，除了这个控制通信序列之外，还提供了所提供的燃料的量的变化率。 燃料量的增加率由燃油控制系统的当前运行功能决定。 然而，由于一般的负载抑制和回复特性以及浪涌的突然特性，燃料流量的变化率非常高。 燃料对燃烧器的快速增加可能导致温度的危险偏移，导致燃气轮机元件的高温。 因此，在燃料控制系统的操作中增加了新的功能，从而实现了对燃料增加速率的改进的调节。 该新功能接收到已检测到浪涌或负载变化的信号。 接下来，信号被传送到燃料阀致动器，调节到燃烧器的燃料，从而对动力涡轮机供电，从而防止超速。 之后，燃料阀的变化率被限制一段时间。 一旦恢复完成，燃料阀的变化率逐渐恢复到正常的运行状态。

公开(公告)号：US5609465A

公开(公告)日：1997-03-11

申请号：US533517

申请日：1995-09-25

Applicant: Brett W. Batson ,  Byron K. Broussard

Inventor： Brett W. Batson ,  Byron K. Broussard

IPC: F01D17/06 ,  F02C9/28

CPC classification number: F02C9/28 ,  F01D17/06 ,  F05D2270/02 ,  F05D2270/053

Abstract: A method and apparatus are disclosed for controlling the rotational speed of gas and steam turbines, and hot gas expanders, with each of these drivers driving a rotational load by way of a shaft. To accomplish this control technique, it is necessary to easily and accurately calculate the amount of power which must be shed by the driver(s) to maintain a constant speed, i.e., neither accelerating nor decelerating. Action must be taken to reduce the power applied to the shaft by this amount. The method incorporates an open-loop approach and uses a time derivative to moderate the open-loop action accordingly.

Abstract translation: 公开了一种用于控制气体和蒸汽涡轮机以及热气体膨胀器的转速的方法和装置，其中每个驱动器通过轴驱动旋转负载。 为了实现这种控制技术，需要容易且准确地计算驾驶员必须减少的功率量，以保持恒定的速度，即既不加速也不减速。 必须采取措施以减少施加在轴上的功率。 该方法结合了开环方法，并使用时间导数来相应地缓和开环动作。

公开(公告)号：US5599161A

公开(公告)日：1997-02-04

申请号：US552788

申请日：1995-11-03

Applicant: Brett W. Batson

Inventor： Brett W. Batson

IPC: F04D27/02 ,  F01D17/00

CPC classification number: F04D27/02 ,  F05B2200/221 ,  Y02P30/48

Abstract: Compressors for processes, as used for refrigeration systems applied to ethylene production, are multiple stage machines; furthermore, sidestreams enter/exit between the stages. Since a flow measurement device is not available between stages, and the gas temperature entering most stages is unknown, it is difficult to calculate an accurate value for reduced flow for antisurge control purposes. A new method is described, whereby reduced flow alone is replaced by the product of the reduced flow and the equivalent speed. This allows accurate calculation of the distance of the operating point to the surge line since the inlet temperatures into the separate compression units (except the first) are not necessary. The invention described herein can be applied to multistage compression systems for a variety of processes.

Abstract translation: 用于制冷系统应用于乙烯生产的过程压缩机是多级机器; 此外，侧线进入/离开阶段之间。 由于在阶段之间不能使用流量测量装置，并且进入大多数阶段的气体温度是未知的，因此难以计算用于防止血流控制目的的减少的流量的准确值。 描述了一种新的方法，其中减少的流量单独由减少的流量和等效速度的乘积代替。 这允许精确地计算工作点到喘振线的距离，因为进入分离的压缩单元（除了第一个）之外的入口温度是不必要的。 本文描述的发明可以应用于用于各种过程的多级压缩系统。

公开(公告)号：US5699267A

公开(公告)日：1997-12-16

申请号：US398001

申请日：1995-03-03

Applicant: Brett W. Batson ,  Byron K. Broussard

Inventor： Brett W. Batson ,  Byron K. Broussard

IPC: F01D21/02 ,  F01D21/16 ,  F02C9/20 ,  G05D13/62 ,  G05D13/66 ,  G05B13/02

CPC classification number: G05D13/66 ,  F01D21/02 ,  F01D21/16 ,  F02C9/20 ,  G05D13/62 ,  F05D2270/021 ,  F05D2270/091 ,  F05D2270/30

Abstract: A method and apparatus are disclosed for preventing overspeed of a hot gas expander and its resultant load when the load (or a portion of it) is shed suddenly. In this situation, power applied by the expander to the shaft must be reduced, but normal feedback to the speed controller may be too slow to be effective. The load rejection may be sensed by a feedforward system before a significant speed increase is detected by the speed control loop. For this approach, the expander can be instrumented with either a flow measurement device, a downstream pressure, or a downstream temperature. Inlet pressure and inlet temperature are required. The method uses the characteristic map describing the expander (shaft power versus mass flow rate) along with a feedforward control action to anticipate the speed increase. By using dimensional analysis, the characteristic curves will collapse into single curves describing the parameters of reduced flow, reduced power, and pressure ratio. Speed increase can now be largely avoided by employing the resultant values from any of the pairs of reduced power relationships (reduced power versus reduced flow rate squared, reduced power versus pressure ratio, and reduced power versus temperature ratio). The reduced flow rate needed to keep the expander and its loads from increasing speed can now be correlated to a valve position resulting in the reduced flow required to maintain speed. This valve position setpoint is applied as an open loop step change.

Abstract translation: 公开了一种方法和装置，用于当突然脱离负载（或其一部分）时，防止热气体膨胀器的超速及其所产生的负载。 在这种情况下，必须减小由膨胀机施加到轴上的动力，但是对速度控制器的正常反馈可能太慢而无法有效。 在由速度控制回路检测到显着的速度增加之前，可以通过前馈系统来感测负载抑制。 对于这种方法，膨胀机可以用流量测量装置，下游压力或下游温度进行装配。 需要入口压力和入口温度。 该方法使用描述膨胀机的特征图（轴功率对质量流量）以及前馈控制动作来预测速度增加。 通过使用尺寸分析，特征曲线将折叠成描述流量减小，功率和压力比的参数的单曲线。 现在可以通过采用来自任何一对降低功率关系（降低的功率与降低的流量平方，功率降低与压力比以及降低的功率对温度比）的结果值来大大避免速度增加。 现在可以将保持膨胀机及其负载的增加速度所需的减小的流量与阀位置相关联，从而导致维持速度所需的减少的流量。 该阀位置设定值作为开环阶跃变化应用。