Compressor airfoil tip clearance optimization system
A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 9,109,608
- Application Number:
- 13/326,399
- OSTI ID:
- 1210876
- Resource Relation:
- Patent File Date: 2011 Dec 15
- Country of Publication:
- United States
- Language:
- English
Gas turbine engines
|
patent | October 1982 |
Compression section for an axial flow rotary machine
|
patent | February 1983 |
Tip clearance control apparatus for a turbo-machine blade
|
patent | April 1993 |
Gas turbine with axially mutually displaceable guide parts
|
patent | January 2004 |
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