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Title: 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:
;
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1210876
Patent Number(s):
9,109,608
Application Number:
13/326,399
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
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}
}

Patent:

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