초록 ▼

A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The perform

A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The performance of the squeeze test and the application of the results may be individually performed for each of the turbine engines.

대표청구항 ▼

1. A method for calibrating an active clearance control system for a plurality of turbine engines, the method comprising: performing a squeeze test between a tip of a rotor blade and a shroud; andapplying results of the squeeze test to adjust a gap between the tip and the shroud;wherein the performi

1. A method for calibrating an active clearance control system for a plurality of turbine engines, the method comprising: performing a squeeze test between a tip of a rotor blade and a shroud; andapplying results of the squeeze test to adjust a gap between the tip and the shroud;wherein the performing of the squeeze test and the applying of the results is individually performed for each of the turbine engines. 2. The method of claim 1, wherein the applying of the results comprises, for at least a first of the turbine engines, calibrating a control logic for the active clearance control system based on the results of the squeeze test. 3. The method of claim 1, wherein the applying of the results comprises, for at least a first of the turbine engines, recalibrating a control logic for the active clearance control system based on the results of the squeeze test. 4. The method of claim 1, wherein the squeeze test is performed, for at least a first of the turbine engines, while the first of the turbine engines is configured with a test stand. 5. The method of claim 1, wherein the squeeze test is performed, for at least a first of the turbine engines, while the first of the turbine engines is operating during aircraft flight. 6. The method of claim 1, wherein the tip and the shroud radially engage one another during the squeeze test. 7. The method of claim 1, wherein the applying of the results accounts for wear of the shroud during the squeeze test. 8. The method of claim 1, wherein the squeeze test is performed, for at least a first of the turbine engines, after a predetermined interval of operation of the first of the turbine engines. 9. The method of claim 1, wherein the results are applied, for at least a first of the turbine engines, to adjust the gap across a flight envelope of the first of the turbine engines. 10. The method of claim 1, wherein at least a first of the turbine engines comprises a production turbine engine. 11. A turbine engine, comprising: a rotor blade extending to a tip;a shroud radially outboard of the tip; andan active clearance control system configured to perform a squeeze test between the tip and the shroud; andcontrol clearance between the tip and the shroud based on results of the squeeze test;wherein the active clearance control system is operable for recalibration based on performance of another squeeze test. 12. The turbine engine of claim 11, wherein the active clearance control system is further configured to perform an additional squeeze test between the tip and the shroud during inflight operation of the turbine engine; andrecalibrate a control logic of the active clearance control system based on results of the additional squeeze test. 13. The turbine engine of claim 11, further comprising: an apparatus to which the shroud is attached or formed integral with;wherein the active clearance control system is configured to actively control clearance between the tip and the shroud by regulating temperature of the apparatus. 14. The turbine engine of claim 11, further comprising: an apparatus to which the shroud is attached or formed integral with;wherein the active clearance control system is configured to actively control clearance between the tip and the shroud by mechanically reconfiguring the apparatus. 15. The turbine engine of claim 11, wherein the controlling of the clearance based on the results of the squeeze test accounts for wear of the shroud during the squeeze test. 16. A turbine engine, comprising: a rotor blade extending to a tip;a shroud radially outboard of the tip; anda system configured to actively control clearance between the tip and the shroud based on a control logic, the system further configured to recalibrate the control logic. 17. The turbine engine of claim 16, wherein the system is configured to perform a squeeze test between the tip and the shroud; andthe recalibration of the control logic is performed based on the results of the squeeze test. 18. The turbine engine of claim 16, wherein the system is configured to recalibrate the control logic after one or more predetermined intervals of operation of the production turbine engine. 19. The turbine engine of claim 16, further comprising: an apparatus to which the shroud is attached or formed integral with;wherein the system is configured to actively control clearance between the tip and the shroud by regulating temperature of the apparatus. 20. The turbine engine of claim 16, further comprising: an apparatus to which the shroud is attached or formed integral with;wherein the system is configured to actively control clearance between the tip and the shroud by mechanically reconfiguring the apparatus.