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Turbine combustor having a liner

A technology for turbines and bushings, used in engine components, engine cooling, turbine/propulsion cooling, etc., to solve problems such as insufficient cooling of the coolant path

Inactive Publication Date: 2010-12-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Unfortunately, the coolant path may not adequately cool all areas of the gas turbine engine

Method used

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  • Turbine combustor having a liner
  • Turbine combustor having a liner
  • Turbine combustor having a liner

Examples

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Embodiment Construction

[0016] One or more specific embodiments of the present invention will be described below. In an effort to provide a concise description of these embodiments, not all features of an actual implementation may be described in the specification. It should be appreciated that when developing any such actual implementation, as in any engineering or design project, a number of implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with the system-related and Business-related constraints, which may vary between implementations. In addition, it should be understood that such a development effort might be complex and time-consuming, but would nonetheless be a routine undertaking of design, production, and manufacture for those of ordinary skill having the benefit of this disclosure .

[0017] When introducing elements of various embodiments of the invention, the articles "a," "an," "the," and "said" are intended to mean that there ...

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Abstract

The invention relates to a turbine system. In one embodiment, a combustor of a turbine system may include a liner disposed inside the combustor. The lining element may include a heat shield having a mounting stud extending along an axis and a shell having an inner surface oriented towards the heat shield. The shell may include a passage configured to receive the mounting stud, and the mounting stud may include a structure configured to hold the heat shield apart from the inner surface of the shell along the axis of the mounting stud.

Description

technical field [0001] The subject matter disclosed herein relates to gas turbine engines, and more particularly, to heat shields associated with combustors. Background technique [0002] Generally, gas turbine engines combust a mixture of compressed air and fuel to produce hot combustion gases. For example, a set of fuel nozzles may inject air and fuel (eg, propane, natural gas) into the combustor, or may inject fuel into the combustor. As is understood, gas turbine engines include various cooling systems to protect components from the heat of combustion. These cooling systems may include coolant paths and / or heat shields. Unfortunately, the coolant path may not adequately cool all areas of the gas turbine engine. For example, there may be hot spots in some artifacts. Contents of the invention [0003] Embodiments commensurate in scope with the originally claimed invention are summarized below. These embodiments are not intended to limit the scope of the claimed inve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/12F23D14/46
CPCF23R3/60F23R3/002
Inventor K·J·埃德瓦德斯T·E·约翰逊
Owner GENERAL ELECTRIC CO
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