• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method for starting a turbine engine (108) using a turbine temperature gradient control and a turbine engine temperature management system (100) is provided. The system (100) includes a temperature sensor (104), a fuel flow modulator, and a temperature controller. The temperature controller is adapted to limit a rate of change in the fuel flow rate supplied to the turbine engine (108) to a value less than a predetermined maximum rate of change in fuel flow that will reduce a rate of change in temperature and maintain a positive rate of change of the turbine engine and to limit a fuel flow to a value greater than a predetermined minimum flow rate of the fuel which maintains a positive rate of change of the temperature and a positive rate of change of the rotational speed of the engine turbine.
    公开号:FR3027960A1
    申请号:FR1560188
    申请日:2015-10-26
    公开日:2016-05-06
    发明作者:Scott Brian Wright；James Robert Turner
    申请人:Unison Industries LLC；
    IPC主号:
    专利说明:

    [0001] The present invention relates to turbine engine control means and, more particularly, to a method and system for starting a turbine engine using gradient control. inter-turbine temperature (TIT). At least some prior art turbine engine systems monitor temperature signals such as, but not limited to, an inter-turbine temperature (TIT) signal, which is provided by an inter-turbine temperature sensor. disposed between the high pressure turbine and the low pressure turbine in the turbine engine and a temperature signal provided by an exhaust gas temperature sensor (TGE) disposed at the outlet of the low pressure turbine. During start-up or during turbine load changes, the TIT gradient usually varies at a rate determined by many factors relating to the parameters of the combustion process and the physical aspects of the particular configuration of the parts located in the engine. and in the immediate vicinity of the gas circuit in the high pressure turbine and the low pressure turbine. Prior art turbine engines do not influence or control the TIT gradient during a turbine engine start-up phase, but can regulate the allowable temperature to a predetermined maximum. Rapid variation of the TIT gradient may subject the turbine parts to additional stress due to the repetition of thermal shocks.
    [0002] There are in the prior art a few small turbine / turboprop engines using electronic means that effectively monitor the rate of change of the TIT and employ a comparator to determine an overrun regarding the rate of change of the TIT. Based on the overshoot, a binary activation fuel valve is instructed to apply fixed bit reductions of fuel flow if the threshold is exceeded. These fixed reductions, applied suddenly, tend to cause sudden changes in TIT temperature and neutralize acceleration to ground idle speed. These fuel flow actions usually occur several times during the first few seconds of stopping the engine until the TIT gradient reaches equilibrium within a predetermined exceedance threshold. Excessive magnitude, rapid changes and / or fluctuations in the TIT temperature may subject the turbine parts to thermal shocks ultimately resulting in shortened service life and potential damage. In a first embodiment, a turbine engine temperature control system includes a temperature sensor for sensing a turbine engine temperature, a fuel flow modulation valve configured to regulate a fuel flow rate to the engine. turbine, and a temperature controller. The temperature controller is adapted to limit a rate of change in the fuel flow rate supplied to the turbine engine to a value less than a predetermined maximum rate of change in fuel flow that will reduce a rate of change in temperature and maintain a rate of positive variation of a rotational speed of the turbine engine and limit a fuel flow to a value greater than a predetermined minimum flow rate of fuel which will maintain a positive rate of change of the temperature and a positive rate of change of the rotational speed turbine engine. In another embodiment, a method for starting a turbine engine using inter-turbine temperature gradient control (TIT) comprises receiving a signal representing an inter-turbine temperature (TIT). of a turbine engine, determining a rate of change of the TIT and comparing the determined rate of change of the TIT with a predetermined rate of change of the threshold of TIT. The method further includes limiting the result of the comparison to a value less than a predetermined maximum rate of change in a fuel flow rate supplied to the turbine engine that will reduce the rate of change of the TIT and maintain a positive rate of change. a rotational speed of the turbine engine. The method also includes determining a flow rate of the fuel supplied to the turbine engine corresponding to the limited rate of change of the fuel flow, a limitation of the fuel flow determined to a value greater than a predetermined minimum flow rate of the fuel which will maintain a rate of positive variation of the TIT and a positive rate of change of the rotational speed of the turbine engine, and the regulation of a fuel flow rate supplied to the turbine engine according to the determined limited fuel flow rate. In yet another embodiment, a temperature control system for a gas turbine engine includes a temperature sensor, a temperature management driver that includes a temperature change rate error circuit communicating with the temperature sensor. temperature, a fuel flow variation limiter communicating with the temperature variation rate error circuit, and a fuel flow limiter communicating with the fuel flow variation limiter via an integrator circuit . The system also includes a fuel system including a fuel flow modulation valve communicating with the fuel flow restrictor, the fuel flow modulation valve being adapted to regulate a flow of fuel supplied to the turbine engine according to a signal provided by the fuel flow limiter. The invention will be better understood from the detailed study of some embodiments taken by way of nonlimiting examples and illustrated by the appended drawings in which: FIG. 1 is a block diagram of a gradient control system inter-turbine temperature system (TIT) according to an exemplary embodiment of the present invention; FIG. 2 is a graph of the TIT during a start-up example of the turbine engine shown in FIG. 1 and a graph of the fuel flow rate Wf during start-up without the use of the TIT gradient control system shown in FIG. 1; FIG. 3 is a graph of the TIT during a start of the turbine engine shown in FIG. 1 and a graph of the fuel flow rate Wf during start-up according to an exemplary embodiment of the invention; and FIG. 4 is a flow diagram of an inter-turbine temperature control process in the turbine engine shown in FIG. 1. Specific details of various embodiments may be shown in some drawings and not in others. but it's only for convenience. Any detail of any drawing may be cited or claimed in combination with any detail of any other drawing. Unless otherwise indicated, the drawings presented herein are intended to illustrate details of embodiments of the invention. It is believed that these details are applicable in all kinds of systems, including one or more embodiments of the invention. In this way, the drawings are not intended to include all the standard details known to those of ordinary skill in the art as being necessary for carrying out the embodiments described herein. The detailed description below illustrates embodiments of the invention by way of non-limiting example. It is contemplated that the invention broadly applies to analytical and methodical embodiments of fuel flow modulation provided to a fuel engine to limit a rate of change in inter-turbine temperature in applications involving industry, trade and housing. Embodiments of the present invention describe a method of controlling fuel flow in response to excessive inter-turbine temperature gradient conditions with limited variations in the flow rate demanded by the fuel metering device during the engine start phase. The limitation phase is set up so that negative transitions (of speed or temperature) are avoided during start-up during programmed accelerations, by means of an interaction process balancing the duration of the fuel intervention. and the amount of fuel prevented from passing into the fuel dispenser. The implementation is facilitated by preconfigured circuits for the fuel flow in the fuel metering unit and by engine start speed algorithms. Advantages in terms of the mechanical life of the engine through the reduction of thermal stresses during engine starts are expected due to the removal of aggressive temperature transitions experienced during an ordinary start. The method measures the rate of change of the inter-turbine temperature (TIT) of the engine and reduces the flow rate if the rate of change exceeds a maximum threshold. The extent of the reduction in fuel flow, the rate at which the fuel flow is falling and rising, and the ultimate duration of the reduction in fuel flow are all limited by the implementation of the control system to reduce the rate of variation, or gradient, of the temperature without causing a reversal of the temperature (negative gradient) nor stalling the engine (negative variation of the regime of the gas generator). The method actively manages the hot starts of the turbine engine and can ultimately limit the maximum temperatures reached, preventing overruns that could cause immediate or latent damage in the turbomachine. The process extends the life of the turbine engine, allowing longer intervals between scheduled checks and overhauls, resulting in lower operating and maintenance costs. The implementation of the TIT gradient management according to the present method serves to prevent prolonged operation or to reduce the operating time at the moment of a power release of the turbine engine, which creates a discontinuity in the engine response. and does not allow it to accelerate in the required manner. The handling of the fuel flow of the engine is kept within reasonable limits so that the acceleration of the engine is not thwarted in order to regulate the temperature TIT. The following description is made with reference to the accompanying drawings, in which, unless otherwise indicated, the same reference numerals designate like elements in different drawings. Figure 1 is a block diagram of an Inter-Turbine Temperature Gradient (TIT) management system 100. In the exemplary embodiment, an inter-turbine temperature signal (TIT) is provided by an inter-turbine temperature sensor 104 installed between a high pressure turbine 106 and a low pressure turbine 108 of, as a Non-limiting example, a free turbine motor 110. The signal 102 is processed using a differentiator circuit or differentiator 112 to produce a signal 114 representing the rate of change of the TIT (ITT-Dot), the signal ITT-Dot 114 is applied to a comparator 116 where it is compared with a predetermined threshold value 118 of ITT-Dot, which establishes the maximum allowable rate of variation of the TIT. The comparator 116 produces an ITT-Dot error signal 120 which is multiplied by a gain k in an amplifier 122. If the ITT-Dot signal 114 exceeds the threshold value 118 of ITT-Dot, an output signal 124 of the amplifier 122 is negative, which tends to lower the flow (Wf) 126 of the fuel. The rate of reduction of the fuel flow (Wf) 126 is proportional to the measured exceedances represented by the ITT-Dot error signal 120. A first Wf-Dot 128 saturation limiter sets a maximum rate of change for the fuel flow, Wf 126, such that the rate of fuel flow reduction is less than a predetermined maximum which could result in an undesirable response. of TIT. The saturation limited signal WfDot 130 is then processed by an integrator 132 to produce a desired fuel rate signal 134 proportional to the desired rate, Wf 126. A desired rate value, Wf 126, is limited by a second saturation limiter. Delta-Wf 136 (which can be implemented using minima-maxima selectors based on planned limits that vary according to the turbine engine gas engine speed). A gas generator speed detector 137 is used to produce the speed of the turbine engine gas generator. An analog program or memory table 139 contains the choices made according to the speed of the turbine engine gas generator by a maxi-mini selector 141. The second Delta-Wf 136 saturation limiter is designed to prevent the flow signal desired fuel 134 to exceed predetermined limits which are suitably set for the operating mode of the engine. During a start-up phase, where the TIT gradient management system 100 is designed to operate, a lower threshold 138 provides a maximum reduction in fuel flow, Delta-Wf, based on a nominal start rate. A final electronic output signal 140 is converted to actual fuel flow by a motor fuel circuit 142. Fig. 2 is a graph 200 of the TIT during an example of starting the turbine engine 110 (shown in Fig. 1) and a graph 202 of the flow rate Wf of the fuel during startup without the use of the gradient management system 100. TIT. Chart 200 includes an x 204 axis graduated in units of time (seconds) and an γ axis 206 graduated in units of temperature. A curve 208 illustrates the TIT during startup.
    [0003] Chart 202 includes an x 210 axis graduated in units of time (seconds) and an y-axis 212 graduated in units of flow. A curve 214 illustrates the flow rate Wf of the fuel supplied to the turbine engine 110 during start-up. At the time of initial ignition (t0), a TIT gradient 216 (ITT-Dotl) (i.e. slope of curve 208) at t0 normally exceeds a desired threshold (i.e. curve 208 exceeds the threshold). From a comparison of ITT-Dot 216 with the threshold, a binary activated fuel valve on the fuel circuit 142 receives an instruction to create a fixed binary reduction 218 of the fuel flow if the threshold is exceeded. This fixed reduction 218, applied suddenly, tends to cause abrupt changes in TIT curve 208 and to neutralize the acceleration of the engine to ground idle speed. Similarly, if the TIT recovers after a fuel flow restoration, a TIT gradient (ITT-Dot2) 220 again exceeds the threshold, causing the binary activation fuel valve on the fuel circuit 142 to close again when a fixed reduction 222 of the fuel flow. The TIT is reduced again before the comparator can open the binary activation fuel valve, which restores the fuel flow and increases the TIT. These rate reductions 218, 222 and 224 typically occur several times during the first few seconds of engine ignition until the TIT gradient reaches equilibrium within the predetermined exceedance threshold. Fig. 3 is a graph 300 of the TIT during a start of the turbine engine 110 (shown in Fig. 1) and a graph 302 of the fuel flow Wf during starting according to an exemplary embodiment of the present invention. Chart 300 includes an x 304 axis graduated in units of time (seconds) and a y-axis 306 graduated in units of temperature. Curve 308 illustrates the TIT during startup. Chart 302 includes an x 310 axis graduated in units of time (seconds) and a Y axis 312 graduated in units of flow. A curve 314 illustrates the flow rate Wf of the fuel supplied to the turbine engine 110 during start-up. The TIT gradient management system 100 is, among many others, a control element which comprises an Electronic Engine Control (EMC) (not shown) for the turbine engine 110, which may include a speed control driver. gas generator, fuel flow limiters programmed to initiate flow and over-speed prevention, and other limit function controllers (eg for torque, TIT value or speed of operation). propeller). EMC determines, among this plurality of controllers, which produces an output signal through a min-max selection process. The results of this solution are illustrated in Figure 3.
    [0004] At the time of initial ignition (t0) of the turbine engine 110, a TIT gradient (ITT-Dotl) 316 at θ typically exceeds a desired threshold (i.e., the slope of the curve 308 exceeds threshold). The EMC, using this method, performs a calculated reduction in fuel flow, Wf, limited by the first Wf-Dot saturation limiter 128 and the second DeltaWf saturation limiter 136, until the closed-loop control. confirms that a TIT gradient (ITT-Dot2) 318 has fallen below the exceedance threshold.
    [0005] Rather than a series of abrupt bit reductions in fuel flow to reduce the TIT gradient during start-up, the present method uses a calculated reduction to act in a controlled manner on the rate of change of the TIT to ensure a smooth transition from the TIT of cold iron temperatures to the ground idle speed of the turbine engine 110. The TIT gradient management system 100 measures the rate of change of the inter-turbine temperature (TIT) of the engine and reduces fuel flow if the rate of change exceeds a maximum threshold. The extent of the reduction in fuel flow, the rate at which the fuel flow is falling and rising, and the ultimate duration of the reduction in fuel flow are all limited by the implementation of the control system to reduce the rate of variation, or gradient, of the temperature without causing a reversal of the temperature (negative gradient) nor stalling the engine (negative variation of the regime of the gas generator). Figure 4 is a flowchart of a method 400 for managing inter-turbine temperature in a turbine engine 110 (shown in Figure 1). In the exemplary embodiment, the method 400 includes receiving 402 a signal representing an inter-turbine temperature (TIT) of a turbine engine, determining 404 a rate of change of the TIT, the comparing 406 the determined rate of change of the TIT with a predetermined rate of change of the TIT, and the limitation 408 of the result of the comparison to a value less than a predetermined maximum rate of change of a fuel flow rate supplied to the engine to turbine, which will reduce the rate of change of the TIT and maintain a positive rate of change of a rotational speed of the turbine engine. The method 400 also comprises determining 410 a fuel flow rate supplied to the turbine engine, corresponding to the limited rate of change of the fuel flow, the limitation 412 of the fuel flow determined to a value greater than a predetermined minimum flow rate of the fuel which maintains a positive rate of change of the TIT and a positive rate of change of the rotational speed of the turbine engine. The method 400 further comprises regulating 414 a fuel flow rate supplied to the turbine engine according to the determined limited fuel flow rate.
    [0006] Embodiments, described above, of a method and system for controlling fuel flow in response to excessive inter-turbine temperature gradient conditions during the turbine engine start-up phase is an economical means. and reliable to avoid negative transitions (in speed or temperature) during scheduled accelerations during the turbine engine start-up phase. More particularly, the methods and systems described herein contribute to a balance between the timing of the intervention on the fuel and the amount of fuel retained using the fuel dispenser. In addition, the methods and systems described above facilitate the measurement of the rate of change of the inter-turbine temperature (TIT) of the engine and the reduction of the flow rate if the rate of change exceeds a maximum threshold. The extent of the reduction in fuel flow, the rate at which the fuel flow is falling and rising, and the ultimate duration of the reduction in fuel flow are all limited by the implementation of the control system to reduce the rate of variation, or gradient, of the temperature without causing a reversal of the temperature (negative gradient) nor stalling the engine (negative variation of the regime of the gas generator). In this way, the methods and systems described herein actively, economically and reliably facilitate the management of turbine engine starts and the limitation of the maximum temperatures achieved, by preventing overruns that could cause immediate damage. or latent in the turbine engine. According to one embodiment of the invention, the temperature management system comprises a fuel circuit designed to regulate a fuel flow rate value supplied to the turbine engine, and the temperature sensor is disposed between a first turbine and a second turbine engine turbine. According to another characteristic of the invention, the temperature controller is further adapted to integrate the limited rate of change signal of the fuel flow to produce a fuel flow signal. According to another characteristic of the invention, the temperature controller is further adapted to transmit the limited rate of change of the fuel flow rate signal to said fuel flow modulation valve. According to another characteristic of the invention, the temperature controller comprises a processor communicating with a memory. According to another characteristic of the invention, the received signal representing a temperature in the gas circuit of a turbine engine is an inter-turbine temperature signal provided by a sensor disposed between a high pressure turbine and a low pressure turbine. . According to another characteristic of the invention, the determination of a variation rate of a fuel flow comprises a comparison of the rate of variation of the temperature with a predetermined maximum rate of variation of the temperature. According to another characteristic of the invention, the determination of a rate of change of a fuel flow comprises a limitation of the rate of change of the fuel flow rate to a predetermined maximum rate of change of the fuel flow. According to an embodiment of the method for starting a turbine engine, the method further comprises determining the flow rate of the fuel supplied to the turbine engine, corresponding to the limited rate of variation of the fuel flow, comprising the integration the determined flow rate of the fuel supplied to the turbine engine. According to one embodiment of the invention, the temperature management system for a gas turbine engine device comprises: a temperature sensor; a temperature management controller comprising: a temperature change rate error circuit communicating with said temperature sensor; a fuel rate variation rate limiter communicating with said rate of change of temperature error circuit; a fuel flow limiter communicating with said fuel flow rate rate limiter via an integrator circuit; and a fuel system comprising a fuel flow modulator communicating with said fuel flow restrictor, said fuel flow modulator being adapted to regulate a flow of fuel supplied to the turbine engine based on a signal provided by said fuel flow limiter. fuel flow.
    [0007] According to another embodiment of the invention, the temperature sensor is disposed in a gas circuit of a gas turbine engine between a high pressure turbine and a low pressure turbine. According to another characteristic of the invention, the temperature variation rate error circuit comprises a diverter circuit designed to generate a rate of change of the temperature and a comparator arranged to produce an error signal representing a difference between a temperature change rate threshold value and the rate of change generated by ra temperature. According to one embodiment of the invention, the temperature management system for a gas turbine engine device further comprises an amplifier designed to convert into a fluid flow rate variation rate signal a rate error signal. temperature variation provided by said temperature change rate error circuit, the fuel rate change rate signal corresponding to a magnitude of a determined change in fuel flow rate to attenuate the signal of temperature change rate error, maintain a positive rate of change in temperature and maintain a positive rate of change in the rotational speed of the turbine engine. According to another characteristic of the invention, the fuel flow rate variation limiter is designed to limit said rate of change of fuel flow, so that the rate of reduction of the fuel flow rate is lower than a predetermined maximum, the maximum rate of change for the fuel flow based at least partially on fuel flow characteristics and on an inertia model for the turbine engine. According to another embodiment of the invention, the fuel flow limiter is designed to limit the fuel flow in order to maintain a positive rate of change in temperature and to maintain a positive rate of change in the speed of rotation of the fuel. turbine engine. According to another embodiment of the invention, the fuel flow limiter comprises a model of the flow characteristics of the fuel circuit and an inertia model for the turbine engine. Examples of methods and systems for managing a TIT gradient in a turbine engine are described in detail above. The illustrated system is not limited to the embodiments described herein; on the contrary, elements of each of them can be used independently and separately from other elements described herein. Each element of the system can also be used in combination with elements of other systems.
    [0008] Tag Legends Tif 100 Gradient Management System TIT 102 Signal Turbine Temperature Sensor 104 High Pressure Turbine 106 Low Pressure Turbine 108 Turbine Engine 110 Derivative Circuit 112 1.0 ITT-Dot Signal 114 Comparator 116 Threshold Value 118 Signal Error 120 Amplifier 122 15 Output Signal 124 Fuel Flow Wf 126 Saturation Limiter 128 Wf-Dot Signal 130 Integrator 132 20 Fuel Flow Signal 134 Overload Limiter 136 Gas Generator Speed Detector 137 Threshold 138 Program Table or of memory 139 25 Output signal 140 Mid-maximum selector 141 Fuel circuit 142 Figure 200
    权利要求:
    Claims (22)
    [0001]
    REVENDICATIONS1. A turbine engine temperature management system (100), comprising: a temperature sensor (104) for detecting a temperature of a turbine engine (110); a fuel rate modulation valve adapted to regulate a fuel flow rate supplied to the turbine engine (110); and a temperature controller adapted to: limit a rate of change in the flow (126) of the fuel supplied to the turbine engine (110) to a value less than a predetermined maximum rate of change in fuel flow which will reduce a rate of change of the temperature and maintain a positive rate of change of a rotational speed of the turbine engine; and limiting a fuel flow rate to a value greater than a predetermined minimum fuel rate of change that maintains a positive rate of temperature change and a positive rate of change in the rotational speed of the turbine engine (110). 20
    [0002]
    The system (100) of claim 1, wherein the temperature controller is adapted to: receive a signal representing a temperature detected by said temperature sensor (104); determining a rate of change of the detected temperature signal; and comparing the determined rate of change of the detected temperature signal with a predetermined temperature change rate threshold (118) to produce a temperature change rate error signal.
    [0003]
    The system (100) of claim 2, wherein said temperature controller is further adapted to determine, using a derivation circuit (112), a rate of change of the detected temperature signal.
    [0004]
    The system (100) of claim 2, wherein said temperature controller is further adapted to apply a predetermined gain to the temperature change rate error signal (120) to produce a corresponding rate of change signal. fuel flow.
    [0005]
    The system (100) of claim 1, wherein said temperature management system includes a fuel circuit (142) adapted to regulate a value of the flow (126) of fuel supplied to the turbine engine (110), the sensor temperature sensor (104) being disposed between a first turbine (106) and a second turbine (108) of the turbine engine (110).
    [0006]
    The system (100) of claim 1, wherein said temperature controller is further adapted to integrate the limited rate of change of fuel flow rate signal (134) to produce a fuel flow signal.
    [0007]
    The system (100) of claim 1, wherein said temperature controller is further adapted to transmit the limited rate of change of fuel flow rate signal to said fuel rate modulation valve.
    [0008]
    The system (100) according to claim 1, wherein said temperature controller is further adapted to limit the determined rate of change in fuel flow and comprises using deminima-maxima selectors (141) in accordance with programmed limits which vary with the speed of the turbine engine gas generator.
    [0009]
    The system (100) of claim 1, wherein said temperature controller comprises a processor communicating with a memory,
    [0010]
    10. A method (400) for starting a turbine engine (110) with a turbine temperature gradient control, said method (400) comprising receiving (402) a temperature signal in the gas circuit of a turbine engine; determining (404) a rate of temperature change; comparing (406) the determined rate of change of temperature with a predetermined rate of change of the temperature threshold; limiting (408) the result of the comparison to a value less than a predetermined maximum rate of change in fuel flow rate supplied to the turbine engine, which will reduce the rate of change in temperature and maintain a positive rate of change a rotational speed of the turbine engine; determining (410) a fuel flow rate supplied to the turbine engine corresponding to the limited rate of change of the fuel flow rate; Limiting (412) the determined fuel flow to a value greater than a predetermined minimum fuel rate which maintains a positive-rate of change in temperature and a positive rate of change in the rotational speed of the turbine engine; andcontrolling (414) a fuel flow rate supplied to the turbine engine based on the determined limited fuel flow rate.
    [0011]
    The method (400) of claim 10, wherein the received signal representing a temperature in the gas circuit of a turbine engine is an inter-turbine temperature signal (TIT) provided by a sensor (104) disposed between a high pressure turbine (106) and a low pressure turbine (108).
    [0012]
    The method (400) of claim 10, wherein determining a rate of change of a fuel flow rate comprises comparing the temperature variation ratio with a predetermined maximum rate of temperature change. .
    [0013]
    The method (400) of claim 10, wherein determining a rate of change of a fuel flow rate includes limiting the rate of change of fuel flow rate to a predetermined maximum rate of change in fuel flow rate. .
    [0014]
    The method (400) of claim 10, further comprising determining the fuel flow rate supplied to the turbine engine, corresponding to the limited rate of change in fuel flow, including integrating the determined flow rate of fuel supplied to the engine. turbine.
    [0015]
    The method (400) of claim 10, wherein limiting the determined fuel rate comprises using minima-maxima selectors (141) in accordance with programmed limits that vary with the speed of the gas generator of the fuel. turbine.
    [0016]
    A temperature management system (100) for a gas turbine engine device (110), the system having a temperature sensor (104), a temperature management controller comprising: a rate of change error circuit; temperature communicating with said temperature sensor (104); a fuel rate variation rate limiter communicating with said rate of change of temperature error circuit; a fuel flow limiter communicating with said fuel flow rate rate limiter via an integrator circuit (132); and a fuel circuit (142) comprising a fuel flow modulator communicating with said fuel flow restrictor, said fuel flow modulator being adapted to regulate a fuel flow supplied to the turbine engine based on a supplied signal by said fuel flow limiter. 15
    [0017]
    The system of claim 16, wherein said temperature sensor (104) is disposed in a gas circuit of a gas turbine engine (110) between a high pressure turbine (106) and a low pressure turbine (108). ).
    [0018]
    The system of claim 16 wherein said temperature change rate error circuit comprises a diverter circuit (112) adapted to generate a rate of change of temperature and a comparator (116) adapted to generate a signal error message (120) representing a difference between a temperature change rate threshold value and the generated rate of change of the temperature.
    [0019]
    The system of claim 16, further comprising an amplifier (122) adapted to convert into a fuel rate change rate signal a temperature variance rate error signal (120) provided by said error rate circuit. rate of change in temperature, the fuel rate change rate signal corresponding to a magnitude of a determined change in fuel flow rate to mitigate the temperature change rate error signal, maintain a positive rate of change of the temperature and maintain a positive rate of change in the rotational speed of the turbine engine (110).
    [0020]
    The system of claim 16, wherein said fuel flow rate rate limiter is adapted to limit said rate of change in fuel flow, so that the rate of fuel flow reduction is less than one. predetermined maximum, the maximum rate of change for fuel flow based at least partially on flow characteristics of the fuel system and an inertia model for the turbine engine.
    [0021]
    The system of claim 16, wherein said fuel flow restrictor is adapted to limit fuel flow to maintain a positive rate of change in temperature and maintain a positive rate of change in engine rotational speed. turbine.
    [0022]
    The system of claim 16, wherein said fuel flow restrictor comprises a model of the flow characteristics of the fuel system and an inertia model for the turbine engine.
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    优先权:
    申请号 | 申请日 | 专利标题
    US14/532,829|US20160123232A1|2014-11-04|2014-11-04|Method and system for turbine engine temperature regulation|
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