Annular gas turbine housing component and a gas turbine comprising the component

a gas turbine and housing technology, applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of limited flow speed, which would otherwise be necessitated, and achieve the effect of increasing the flow speed

Inactive Publication Date: 2012-06-07
VOLVO AERO CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0012]Further, by arranging the plurality of circumferentially spaced second channels in a crossing relationship with the plurality of circumferentially spaced first channels, arrange

Problems solved by technology

In other words, a flow speed increase, which

Method used

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  • Annular gas turbine housing component and a gas turbine comprising the component
  • Annular gas turbine housing component and a gas turbine comprising the component
  • Annular gas turbine housing component and a gas turbine comprising the component

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Embodiment Construction

[0024]The invention will below be described for a turbofan gas turbine aircraft engine 1, which in FIG. 1 is circumscribed about an engine longitudinal central axis 2. The engine 1 comprises an outer casing or nacelle 3, an inner casing 4 (rotor) and an intermediate casing 5 which is concentric to the first two casings and divides the gap between them into an inner primary gas channel 6 for the compression of air and a secondary channel 7 in which the engine bypass air flows. The casings are in turn made up of a plurality of components in the axial direction of the engine. Thus, each of the gas channels 6,7 is annular in a cross section perpendicular to the engine longitudinal central axis 2.

[0025]The engine 1 comprises a fan 8 which receives ambient air 9, a booster or low pressure compressor (LPC) 10 and a high pressure compressor (HPC) 11 arranged in the primary gas channel 6, a combustor 12 which mixes fuel with the air pressurized by the high pressure compressor 11 for generati...

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Abstract

The invention relates to an annular gas turbine housing component (15) comprising a plurality of circumferentially spaced first channels (16) for conveying a first gas flow in a first direction and a plurality of circumferentially spaced second channels (17) for conveying a second gas flow in a second direction across the first direction in a crossing position (18) of the first and second channels.

Description

BACKGROUND AND SUMMARY[0001]The present invention relates to an annular gas turbine housing component. The invention is further directed to a gas turbine engine, and especially to an aircraft engine, comprising the component. Thus, the invention is especially, directed to a jet engine.[0002]Jet engine is meant to include various types of engines, which admit air at relatively low velocity, heat it by combustion and shoot it out at a much higher velocity. Accommodated within the term jet engine are, for example, turbojet engines and turbofan engines. The invention will below be described for a turbofan engine, but may of course also be used for other engine types.[0003]An aircraft gas turbine engine of the turbofan type generally comprises a forward fan and booster compressor, a middle core engine, and an aft low pressure power turbine. The core engine comprises a high pressure compressor, a combustor and a high pressure turbine in a serial relationship. The high pressure compressor ...

Claims

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Application Information

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IPC IPC(8): F01D25/24F01D25/08
CPCF01D25/14Y02T50/675F02C7/143Y02T50/60
Inventor JACOBSSON, DENNIS
Owner VOLVO AERO CORP
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