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Liner for a Gas Turbine Engine Combustor

a technology for gas turbine engines and combustor tubes, which is applied in the direction of combustion process, lighting and heating apparatus, climate sustainability, etc., can solve the problems of damage or premature wear of the liner, and achieve the effect of increasing the cooling of the liner

Inactive Publication Date: 2019-08-15
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes a gas turbine engine combustor with improved cooling capabilities. The combustor liner includes a film cooling hole with an outlet on the first side of the liner, and an airflow feature on the first side of the liner adjacent to the outlet to increase cooling. This feature helps to protect the liner from high temperatures during operation of the gas turbine engine. Additionally, the combustor liner may also have other airflow features positioned adjacent to other film cooling holes to further enhance cooling. This design helps to improve the efficiency and durability of gas turbine engines.

Problems solved by technology

Notably, however, hotspots may form around the stream of compressed air flowing through the film cooling holes into the combustion chamber, potentially damaging or prematurely wearing the liner.

Method used

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  • Liner for a Gas Turbine Engine Combustor
  • Liner for a Gas Turbine Engine Combustor
  • Liner for a Gas Turbine Engine Combustor

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Embodiment Construction

[0047]Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.

[0048]As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0049]The terms “forward” and “aft” refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operational attitude of the gas turbine engine or vehicle. For example, with regard to a gas turbine engine, forward refers to a position closer to an engine inlet and aft refers to a position closer to an engine nozzle or exhaust.

[0050]The terms “upstream” and “...

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Abstract

A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner including an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.

Description

FIELD[0001]The present subject matter relates generally to a liner for a gas turbine engine combustor.BACKGROUND[0002]A gas turbine engine typically includes an inlet, one or more compressors, a combustor, and at least one turbine. The compressors compress air which is channeled to the combustor where it is mixed with fuel. The mixture is then ignited for generating hot combustion gases. The combustion gases are channeled to the turbine(s) which extracts energy from the combustion gases for powering the compressor(s), as well as for producing useful work to propel an aircraft in flight or to power a load, such as an electrical generator. For example, in at least certain embodiments, the gas turbine engine may further include a fan driven by the one or more turbines.[0003]Additionally, typical combustion sections include one or more liners defining a combustion chamber. Film cooling holes may be defined within these liners to form a cooling air film on a hot side of the liner to main...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F23R3/00F23R3/16
CPCF23R3/002F23R3/16F23R3/14F23R3/08F23R2900/03042F23R3/06Y02T50/60
Inventor GANDIKOTA, GURUNATH
Owner GENERAL ELECTRIC CO
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