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TURBINE CASE WITH CAST-IN AIR SWIRLERS

IP.com Disclosure Number: IPCOM000250338D
Publication Date: 2017-Jun-29
Document File: 6 page(s) / 154K

Publishing Venue

The IP.com Prior Art Database

Abstract

A turbine case is provided with a set of air swirlers located along its circumference that direct air flow into nozzle and shroud supply cavity of a turbine engine. The swirlers are cast together with the turbine case.

This text was extracted from a PDF file.
This is the abbreviated version, containing approximately 37% of the total text.

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TURBINE CASE WITH CAST-IN AIR SWIRLERS

ABSTRACT

[0001] A turbine case is provided with a set of air swirlers located along its

circumference that direct air flow into nozzle and shroud supply cavity of a turbine

engine. The swirlers are cast together with the turbine case.

BACKGROUND

[0002] This disclosure relates generally to gas turbine engines and more particularly to

cooling in gas turbine engines such as turboprop or turboshaft engines.

[0003] In a typical gas turbine engine, components within the "hot section", i.e.

combustor and high-pressure turbine, are subjected to high-temperature corrosive

combustion gases and must be actively cooled to ensure component integrity and

adequate service life.

[0004] Cooling of hot-section components is typically accomplished by bleeding

relatively lower-temperature air from a source such as the engine's compressor and

directing it through cooling plenums and passages.

[0005] In some engine configurations, the cooling air supply can cause uneven cooling of

components, such as turbine cases, distorting their intended dimensions. Furthermore, in

some instances, the flow path for cooling air can result in an unacceptably large

temperature increase of the cooling air due to contact with hot components upstream of

the intended point of use of the cooling air.

[0006] Described herein is a turbine case including cooling air swirlers formed integrally

therewith in order to provide improved uniformity of cooling.

BRIEF DESCRIPTION OF THE DRAWINGS

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[0007] The concept may be best understood by reference to the following description

taken in conjunction with the accompanying drawing figures in which:

[0008] FIG. 1 is a schematic view of a gas turbine engine;

[0009] FIG. 2 is a schematic front elevational view of a turbine case shown in FIG. 1;

[0010] FIG. 3 is an enlarged view of a portion of FIG. 2; and

[0011] FIG. 4 is a view taken along lines 4-4 of FIG. 2.

DETAILED DESCRIPTION OF THE CONCEPT

[0012] Referring to the drawings wherein identical reference numerals denote the

same elements throughout the various views, FIGS. 1-3 depict an exemplary gas turbine

engine 10 including in sequential flow sequence, a compressor 12, a combustor 14, and a

high-pressure turbine ("HPT") 16. In operation, the compressor 12 provides compressed

air that passes primarily into the combustor 14 to support combustion and partially

around the combustor 14 where it is used to cool both the combustor liners and

turbomachinery further downstream. Fuel is introduced into the forward end of the

combustor 14 and is mixed with the air in a conventional fashion. The resulting fuel-air

mixture flows into the combustor 14 where it is ignited to generate hot combustion gases.

The hot combustion gases are discharged to the HPT 16 where they are expanded so that

energy is extracted. The HPT 16 drives the compressor 12 through a shaft 18. In the

illustrated example, the engine 10 is a turboshaft engine and a low-pressure turbine

("LPT"...