TIP CLEARANCE CONTROL METHOD
First Claim
1. A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine, the method comprising the steps:
- a) performing a first run of the gas turbine engine;
b) shutting down the gas turbine engine;
c) starting the gas turbine engine for a second run;
d) measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run;
e) recording the thermal condition of at least part of the engine in accordance with the measured performance parameters;
f) retrieving the recorded thermal condition and controlling the temperature of the casing during at least part of the second run in a manner dependent on it
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Accused Products
Abstract
A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run. The method further comprises measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run. The thermal condition of at least part of the engine in accordance with the measured performance parameters is then recorded. Finally the recorded thermal condition is retrieved and the temperature of the casing is controlled during at least part of the second run in a manner dependent on it.
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Citations
15 Claims
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1. A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine, the method comprising the steps:
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a) performing a first run of the gas turbine engine; b) shutting down the gas turbine engine; c) starting the gas turbine engine for a second run; d) measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run; e) recording the thermal condition of at least part of the engine in accordance with the measured performance parameters; f) retrieving the recorded thermal condition and controlling the temperature of the casing during at least part of the second run in a manner dependent on it - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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- 11. A tip clearance control system fore controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine, the system comprising at least one sensor each arranged to measure a performance parameter of the engine, a memory arranged to record a thermal condition of at least part of the engine dependent on the measured performance parameters and a processing system arranged to retrieve the recorded thermal condition and control the temperature of the casing in a manner dependent upon it during at least part of a second run, the tip clearance control system being further arranged to measure the performance parameters during or after a first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components. is substantially displaced as a consequence of a second run.
Specification