Shortened support for compressor variable vane

a technology of compressor variable and support, which is applied in the direction of machines/engines, mechanical equipment, liquid fuel engines, etc., can solve the problems of the support being drawn inwardly and away from the vane stem

Inactive Publication Date: 2016-10-13
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text describes a variable vane assembly for a compressor section. The assembly includes an upstream vane stage and a downstream vane stage. The upstream vane stage has an airfoil coupled with an upstream vane stem and an upstream vane arm. The downstream vane stage has an airfoil coupled with a downstream vane stem and a downstream vane arm. The assembly also includes a housing boss for each vane stage. The clearance between the vane arm and the housing boss is defined, and a ratio of the clearance to the outer diameter of the housing boss is greater than 10. The assembly also includes a top hat bushing and a downstream bushing for each vane stage. The technical effects of the patent text include improved airflow and efficiency of the compressor section.

Problems solved by technology

In the prior art, the support for the vane stem is complicated by the possibility that a pressure drop, from outside of the compressor section compared to inside the compressor section, could cause the vane to be drawn inwardly and away from its support.

Method used

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  • Shortened support for compressor variable vane
  • Shortened support for compressor variable vane
  • Shortened support for compressor variable vane

Examples

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Embodiment Construction

[0031]FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.

[0032]The exemplary engine 20 generally includes ...

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Abstract

A variable vane assembly comprises an upstream vane stage including an airfoil coupled with an upstream vane stem and an upstream vane arm, configured to drive the upstream vane stem to rotate. The upstream vane stem is supported in an upstream housing boss. A downstream vane stage includes an airfoil coupled with a downstream vane stem and a downstream vane arm, and configured to drive the downstream vane stem to rotate. The downstream vane stem is supported in a downstream housing boss. A first clearance is defined between a radially inner end of the upstream vane arm and a radially outer end of the upstream housing boss. A second clearance is defined between a radially inner end of the downstream vane arm and a radially outer end of the downstream housing boss. A clearance ratio of the second clearance to the first clearance is greater than or equal to 10.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This application claims priority to U.S. Provisional Patent Application No. 61 / 916,358, filed 16 Dec. 2013.BACKGROUND OF THE INVENTION[0002]This application relates to a support for a vane stem of a compressor variable vane.[0003]Gas turbine engines are known and, typically, include a fan delivering air into a compressor section. The air is compressed and delivered into a combustor section where it is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors driving them to rotate.[0004]In a standard compressor section, there are rotating rotors carrying stages of blades. Between the stages of rotating blades there are often static vanes. One type of vane has an angle of incidence that may be varied to direct the air flow to a downstream blade in a desired condition. An actuator for the variable vane can change the angle depending on flight conditions. It is known to have the actuator driving an airfoil o...

Claims

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Application Information

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Patent Type & AuthorityApplications(United States)
IPC IPC(8): F04D19/02F04D27/00
CPCF04D27/002F04D19/022F01D17/162F04D29/563Y02T50/60
InventorLABOUDY, CRYSTALWOOD, MARK R.TRAVIS, BRITTANY
OwnerUNITED TECH CORP