Compressor airfoil tip clearance optimization system
Abstract
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.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1210876
- Patent Number(s):
- 9109608
- Application Number:
- 13/326,399
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F04 - POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS F04D - NON-POSITIVE-DISPLACEMENT PUMPS
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2011 Dec 15
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Little, David A., and Pu, Zhengxiang. Compressor airfoil tip clearance optimization system. United States: N. p., 2015.
Web.
Little, David A., & Pu, Zhengxiang. Compressor airfoil tip clearance optimization system. United States.
Little, David A., and Pu, Zhengxiang. Tue .
"Compressor airfoil tip clearance optimization system". United States. https://www.osti.gov/servlets/purl/1210876.
@article{osti_1210876,
title = {Compressor airfoil tip clearance optimization system},
author = {Little, David A. and Pu, Zhengxiang},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {8}
}
Works referenced in this record:
Gas turbine engines
patent, October 1982
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- US Patent Document 4,354,687
Compression section for an axial flow rotary machine
patent, February 1983
- Walsh, Thomas C.
- US Patent Document 4,371,311
Tip clearance control apparatus for a turbo-machine blade
patent, April 1993
- Evans, David H.
- US Patent Document 5,203,673
Gas turbine with axially mutually displaceable guide parts
patent, January 2004
- Scholz, Christian; Tiemann, Peter
- US Patent Document 6,676,372