[특허]High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control

United Technologies Corporation

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특허 상세정보

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High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-007/00 G05D-011/00 G06G-007/70
미국특허분류(USC)	700/282; 415/173.2; 415/115; 701/100; 600/782
출원번호	US-0552656 (2009-09-02)
등록번호	US-8315741 (2012-11-20)
발명자 / 주소	Karpman, Boris Meisner, Richard P. Shade, John L.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 11 인용 특허 : 64

초록
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A system comprises a rotary apparatus, a control law and a processor. The rotary apparatus comprises a rotor and a housing forming a gas path therebetween, and the control law controls flow along the gas path. The processor comprises an output module, a plurality of temperature modules, a thermodynamic module, a comparator and an estimator. The output module generates an output signal as a function of a plurality of rotor and housing temperatures defined along the gas path, and the temperature modules determine time derivatives of the rotor and housing temperatures. The thermodynamic module models boundary conditions for the gas path, and the comparator determines errors in the boundary conditions. The estimator estimates the rotor and housing temperatures based on the time derivatives, such that the errors are minimized and the flow is controlled.

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1. A system comprising: a rotary apparatus comprising a rotor and a housing, the rotor and the housing forming a gas path therebetween;a control law for controlling flow along the gas path; anda processor for generating an output to direct the control law, the processor comprising: an output module for generating the output as a function of a plurality of rotor and housing temperatures defined along the gas path;a plurality of temperature modules for determining time derivatives of the rotor and housing temperatures;a thermodynamic module for modeling boundary conditions along the gas path, based on the rotor and housing temperatures;a comparator for determining errors in the boundary conditions; andan estimator for estimating the rotor and housing temperatures based on the time derivatives, such that the errors are minimized and the flow is controlled along the gas path;wherein the output comprises a heat transfer signal based on heat transfer from the flow to the rotary apparatus, and wherein the control law controls the flow along the gas path by controlling fuel flow to the rotary apparatus based on the heat transfer signal. 2. The system of claim 1, wherein the estimator comprises a single-input, single-output gain matrix that relates each of the temperature states to exactly one of the time derivatives. 3. The system of claim 1, wherein the boundary conditions comprise an inlet temperature, an inlet pressure, an exit temperature and an exit pressure, and wherein the thermodynamic module models the exit temperature based on the inlet temperature and the rotor and housing temperatures. 4. The system of claim 1, further comprising an actuator for regulating the fuel flow to the rotary apparatus, and wherein the control law limits thrust by directing the actuator to limit the fuel flow. 5. The system of claim 1, wherein the output comprises a clearance signal and the control law controls the flow by controlling clearance along the gas path, based on the clearance signal. 6. The system of claim 5, wherein the function of the rotor and housing temperatures is also a function of a rotational speed of the rotor, such that the output module generates the clearance signal based on the rotor and housing temperatures and a spool speed of the rotary apparatus. 7. The system of claim 6, further comprising an actuator for regulating coolant flow onto the housing, and wherein the control law maintains the clearance within an operational range by directing the actuator to regulate the coolant flow onto the housing. 8. The system of claim 6, wherein the rotor comprises a plurality of rotor blades and the function of the rotor and housing temperatures comprises a coefficient of thermal expansion of the housing, such that the output module generates the clearance signal based on spacing between the rotor blades and the housing. 9. The system of claim 6, wherein the housing comprises a plurality of stator vanes and the function of the temperature states comprises a coefficient of thermal expansion of the rotor, such that the control signal is based on spacing between the stator vanes and the rotor. 10. A method for controlling flow along a gas path between a rotor and a housing, the method comprising: modeling boundary conditions along the gas path, wherein the boundary conditions comprise an inlet temperature, and inlet pressure, an exit temperature and an exit pressure;determining errors in the boundary conditions, based on thermodynamic constraints along the flow path;modeling material temperatures for a plurality of rotor and housing materials along the gas path, based on the inlet temperature;generating a control signal based on the material temperatures and on coefficients of thermal expansion of the rotor and housing materials;determining time rates of change of the material temperatures, based on heat transfer along the gas path;controlling the flow based on the control signal, such that the boundary conditions are maintained within an operational range; andupdating the material temperatures based on the time rates of change, such that the errors in the boundary conditions are minimized. 11. The method of claim 10, wherein updating the material temperatures based on the time rates of change is performed such that the time rates of change are minimized. 12. The method of claim 10, wherein controlling the flow comprises regulating a coolant flow based on the control signal, such that clearance is maintained between the rotor and the housing. 13. The method of claim 12, wherein generating the control signal comprises generating a clearance control signal based on the material temperatures, the coefficients of thermal expansion, a spool speed of the rotor and an internal pressure within the housing. 14. The method of claim 10, wherein controlling the flow comprises regulating a fuel flow based on the control signal, such that a compressor stall margin is controlled for the rotor. 15. The method of claim 14, wherein generating the control signal comprises generating a heat transfer signal based on the material temperatures and specific heats of the rotor and housing materials. 16. A turbine comprising: a rotor having a plurality of rotor blades extending radially therefrom;a casing positioned about the rotor blades, such that a gas path is formed between the rotor and the casing;a valve actuator for maintaining clearance along the gas path by regulating cooling fluid flow onto the casing; anda controller for directing the valve actuator based on a control signal, the controller comprising: a control module for generating the control signal as a function of a plurality of rotor and casing temperatures defined along the gas path;a plurality of temperature modules for determining time derivatives of the rotor and casing temperatures;a thermodynamic module for modeling boundary conditions for the gas path, based on the rotor and casing temperatures;a comparator for determining errors in the boundary conditions, based on thermodynamic flow constraints; andan estimator for estimating the rotor and casing temperatures based on the time derivatives, such that the errors in the boundary conditions are minimized and the clearance is maintained. 17. The system of claim 16, wherein the control module generates the control signal as a function of the rotor and casing temperatures and a rotational speed of the rotor, such that the control signal accounts for centripetal acceleration of the rotor blades. 18. The system of claim 17, wherein the control module generates the control signal as a function of specific heats of the rotor and the casing, such that the control signal accounts for thermal transfer along the gas path. 19. The system of claim 18, further comprising a flow actuator for limiting thrust by regulating fuel flow to the turbine, based on the thermal transfer. 20. A system comprising: a rotary apparatus comprising a rotor and a housing, the rotor and the housing forming a gas path therebetween;a control law for controlling flow along the gas path; anda processor for generating an output to direct the control law, the processor comprising: an output module for generating the output as a function of a plurality of rotor and housing temperatures defined along the gas path;a plurality of temperature modules for determining time derivatives of the rotor and housing temperatures;a thermodynamic module for modeling boundary conditions along the gas path, based on the rotor and housing temperatures;a comparator for determining errors in the boundary conditions; andan estimator for estimating the rotor and housing temperatures based on the time derivatives, such that the errors are minimized and the flow is controlled along the gas path;wherein the output comprises a clearance signal and the control law controls the flow by controlling clearance along the gas path, based on the clearance signal;wherein the function of the rotor and housing temperatures is also a function of a rotational speed of the rotor, such that the output module generates the clearance signal based on the rotor and housing temperatures and a spool speed of the rotary apparatus; andwherein the housing comprises a plurality of stator vanes and the function of the temperature states comprises a coefficient of thermal expansion of the rotor, such that the control signal is based on spacing between the stator vanes and the rotor.

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High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control

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High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control

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