[특허]Compressor tip clearance management for a gas turbine engine

UNITED TECHNOLOGIES CORPORATION

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특허 상세정보

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Compressor tip clearance management for a gas turbine engine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-011/20 F01D-011/08 F04D-027/00 F04D-029/16 F04D-029/56 F02C-009/20 F04D-027/02
출원번호	US-0487632 (2012-06-04)
등록번호	US-9097133 (2015-08-04)
발명자 / 주소	Dong, Yuan Brilliant, Lisa I. Carminati, Daniel Sirica, Steven J.
출원인 / 주소	UNITED TECHNOLOGIES CORPORATION
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 2 인용 특허 : 12

초록
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A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure ...

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1. A method of managing a tip clearance in a high pressure compressor on a high spool, wherein a low spool includes a low pressure compressor, comprising the steps of: identifying a high pressure compressor clearance condition; andadjusting a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor;thereby altering a high pressure compressor rotor speed with the variable stator vane for changing the high pressure compressor clearance condition. 2. The method according to claim 1, wherein the high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor rotor blade tips that is outside a predetermined clearance range. 3. The method according to claim 2, wherein a tip clearance is electronically calculated, by a controller, based on predictive determinations and/or sensed conditions of the high pressure compressor. 4. A method of managing a tip clearance in a high pressure compressor on a high spool, wherein a low spool includes a low pressure compressor, comprising the steps of: identifying a high pressure compressor clearance condition;adjusting a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor;thereby altering a high pressure compressor rotor speed with the variable stator vane for changing the high pressure compressor clearance condition;the high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor rotor blade tips that is outside a predetermined clearance range;the high pressure compressor clearance condition is a tip clearance that is less than a predetermined minimum clearance, thereby anticipating a blade rub condition; andthe adjusting step includes the step of closing the variable stator vanes;thereby decreasing the high pressure compressor rotor speed for increasing clearance between the engine static structure and the high pressure compressor rotor blade tips. 5. A method of managing a tip clearance in a high pressure compressor on a high spool, wherein a low spool includes a low pressure compressor, comprising the steps of: identifying a high pressure compressor clearance condition;adjusting a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor;thereby altering a high pressure compressor rotor speed with the variable stator vane for changing the high pressure compressor clearance condition;the high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor rotor blade tips that is outside a predetermined clearance range;the high pressure compressor clearance condition is a tip clearance that is greater than a predetermined maximum clearance; andthe adjusting step includes opening the variable stator vanes;thereby increasing the high pressure compressor rotor speed for decreasing clearance between the engine static structure and the high pressure compressor rotor blade tips. 6. A compressor tip clearance management system comprising: a compressor section including a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor;a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor, the variable stator vane connected to an actuator; andan electronic controller in communication with the actuator, the controller configured to command the actuator to move the variable stator vane in response to a high pressure compressor clearance condition, to thereby alter a high pressure compressor rotor speed and change the high pressure compressor clearance condition. 7. The system according to claim 6, comprising: an engine static structure; andthe high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor rotor blade tips that is outside a predetermined clearance range. 8. The system according to claim 6, wherein: the controller communicates with an electronic clearance control module that determines the high pressure compressor clearance condition, based on predictive determinations and/or sensed conditions of the high pressure compressor. 9. The system according to claim 8, comprising sensors in communication with the controller configured to provide characteristics relating to the high pressure compressor. 10. The system according to claim 9, wherein: at least one of said sensors is a rotational speed sensor; andthe high pressure compressor condition is predicted based on the sensed rotational speed of the high pressure compressor. 11. The system according to claim 6, comprising: plural shafts, including an inner shaft and an outer shaft; andthe low pressure compressor and the high pressure compressor are respectively mounted to the inner and outer shafts. 12. The system according to claim 11, comprising: a fan section; anda geared architecture operatively coupling the inner shaft to the fan section. 13. The system according to claim 12, wherein: the fan section is arranged in a bypass flow path and is configured to provide a bypass ratio greater than six, and the geared architecture provides a gear reduction ratio of at least 2.3. 14. A compressor tip clearance management system comprising: a compressor section including a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor;a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor, the variable stator vane connected to an actuator;an electronic controller in communication with the actuator, the controller configured to command the actuator to move the variable stator vane in response to a high pressure compressor clearance condition, to thereby alter a high pressure compressor rotor speed and change the high pressure compressor clearance condition;an engine static structure;the high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor blade tips that is outside a predetermined clearance range;the high pressure compressor clearance condition is a tip clearance that is less than a predetermined minimum clearance, thereby anticipating a blade rub condition; andthe controller command closes the variable stator vane, thereby decreasing the high pressure compressor rotor speed and increasing clearance between the engine static structure and the high pressure compressor rotor blade tips. 15. A compressor tip clearance management system comprising: a compressor section including a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor;a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor, the variable stator vane connected to an actuator;an electronic controller in communication with the actuator, the controller configured to command the actuator to move the variable stator vane in response to a high pressure compressor clearance condition, to thereby alter a high pressure compressor rotor speed and change the high pressure compressor clearance condition;an engine static structure;the high pressure compressor clearance condition corresponds to a clearance between an engine static structure and high pressure compressor rotor blade tips that is outside a predetermined clearance range;the high pressure compressor clearance condition is a tip clearance that is greater than a predetermined maximum clearance; andthe controller command opens the variable stator vanes, thereby increasing the high pressure compressor rotor speed and decreasing clearance between the engine static structure and the high pressure compressor rotor blade tips.

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 2

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Compressor tip clearance management for a gas turbine engine

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Compressor tip clearance management for a gas turbine engine

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