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Turbine engine and method of assembling thereof

A turbine engine and turbine technology, applied in the direction of engine components, machines/engines, gas turbine devices, etc., can solve the problems of increasing the inefficiency of gas turbine operation, increasing the weight, cost and complexity of gas turbines

Inactive Publication Date: 2016-06-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, utilizing the first and second sets of guide vanes to redirect the flow of air and combustion gases increases the operational inefficiency of the gas turbine
Furthermore, the inclusion of additional components, such as the first and second sets of guide vanes, generally increases the weight, cost and complexity of the gas turbine

Method used

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  • Turbine engine and method of assembling thereof
  • Turbine engine and method of assembling thereof
  • Turbine engine and method of assembling thereof

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Embodiment Construction

[0066] In the following specification and claims, reference will be made to various terms which shall be defined to have the following meanings.

[0067] The singular forms "a", "an" and "the" include plural reference unless the context clearly dictates otherwise.

[0068] "Optional" or "optionally" means that the subsequently described event or circumstance may or may not occur, and that the description includes instances where the event occurs and instances where it does not.

[0069] Approximate language, as used herein throughout the specification and claims, may be used to modify any quantitative representation, which may permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms such as "about", "approximately" and "substantially" is not to be limited to the precise value specified. In at least some instances, the approximate language may correspond to the precision of the tool applied to...

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PUM

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Abstract

A turbine engine (10) is provided. The turbine engine (10) includes a compressor (14) configured to discharge a flow of air (104) at a first flow angle and a combustor (16) coupled downstream from the compressor (14). The combustor (16) is configured to combust the flow of air (104) with fuel to form a flow of combustion gas (106) discharged from the combustor (16) at a second flow angle. The turbine engine (10) also includes a turbine (18) coupled downstream from the combustor (16). The turbine (18) includes an inlet (122) configured to receive the flow of combustion gas (106) having a flow angle within a predetermined range, wherein the combustor (16) is oriented such that the second flow angle is within the predetermined range.

Description

[0001] Cross References to Related Applications [0002] This application claims the benefit of US Provisional Patent Application Serial No. 61 / 989,855, entitled "Overcompact Combustor," filed May 7, 2014, the entire contents of which are incorporated herein by reference. technical field [0003] The present disclosure relates generally to turbine engines, and more particularly to improved turbine engine component structures utilizing swirl combustion, such as those found in overcompact combustors. Background technique [0004] Rotating machines such as gas turbines are commonly used to generate power using electrical generators. A gas turbine, for example, has a gas path that typically includes an air inlet, a compressor, a combustor, a turbine, and an exhaust pipe in continuous flow relationship. The compressor and turbine sections include at least one set of circumferentially spaced rotating buckets or blades coupled within a casing. At least some known turbine engines...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/14
CPCF02C3/14F01D9/023F04D27/0246F04D29/544F04D29/563F05D2240/35F23R3/12F23R3/26F23R3/28F23R3/50F23R3/04Y10T29/49323B23P15/04F02C3/04F04D29/542F23R3/002F23R3/14F23R3/34F23R3/44
Inventor P.D.西尔科夫斯基
Owner GENERAL ELECTRIC CO