Wall section for the working gas annulus of a gas turbine engine

Inactive Publication Date: 2014-10-02
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0007]It would be desirable to provide improved attachment of a wall section

Problems solved by technology

However, such an assembly approach is problematic to implement in a ceramic matrix composite

Method used

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  • Wall section for the working gas annulus of a gas turbine engine
  • Wall section for the working gas annulus of a gas turbine engine
  • Wall section for the working gas annulus of a gas turbine engine

Examples

Experimental program
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Embodiment Construction

[0033]With reference to FIG. 1, a ducted fan gas turbine engine generally indicated at 10 has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, and intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.

[0034]The gas turbine engine 10 works in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the air flow

[0035]A directed into it before delivering that air to the hig...

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PUM

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Abstract

A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment has two or more spaced passageways. In use, a respective support bar can be contained within each passageway. The support bars allow attachment of the seal segment to the engine casing. Each passageway has an elliptical or substantially elliptical cross-section with a minor diameter and a major diameter, the minor diameter being substantially aligned with the radial direction. The respective support bar has a correspondingly elliptical or substantially elliptical cross-section for a close fit in the passageway.

Description

FIELD OF THE INVENTION[0001]The present invention relates to a wall section for the working gas annulus of a gas turbine engine, such as a seal segment for a shroud ring of a rotor of a gas turbine engine, and particularly, but not exclusively, to such a wall section which is formed of ceramic.BACKGROUND OF THE INVENTION[0002]The performance of gas turbine engines, whether measured in terms of efficiency or specific output, is improved by increasing the turbine gas temperature. It is therefore desirable to operate the turbines at the highest possible temperatures. For any engine cycle compression ratio or bypass ratio, increasing the turbine entry gas temperature produces more specific thrust (e.g., engine thrust per unit of air mass flow). However, as turbine entry temperatures increase, it is necessary to develop components and materials better able to withstand the increased temperatures.[0003]This has led to the replacement of metallic shroud segments with ceramic matrix composi...

Claims

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Application Information

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IPC IPC(8): F01D25/28F01D11/08
CPCF01D11/08F01D25/28F01D11/122F05D2240/11F05D2260/30F05D2300/603F05D2300/6033F05D2250/14F05D2260/311F05D2240/91
Inventor HILLIER, STEVENWONG, ALEX
Owner ROLLS ROYCE PLC
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