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Gas turbine including multiple can combustors

A gas turbine and combustor technology, applied in the field of interaction, can solve problems such as the separation plane sealing of the casing that cannot be guaranteed

Active Publication Date: 2021-12-14
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the above case, the sealing of the separation plane of the enclosure cannot be guaranteed during transient operation

Method used

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  • Gas turbine including multiple can combustors
  • Gas turbine including multiple can combustors
  • Gas turbine including multiple can combustors

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Embodiment Construction

[0030] With reference to the accompanying drawings, the technical content and detailed description of the present invention are described below according to the preferred embodiments, and the preferred embodiments are not intended to limit the implementation scope of the present invention. Any equivalent changes and modifications made according to the appended claims are all covered by the claims of the present invention.

[0031] The present invention will now be described in detail with reference to the accompanying drawings.

[0032] refer to figure 1 , which is a schematic diagram of a gas turbine used in a power plant. according to figure 1 As an example, a gas turbine 1 includes a compressor 2 , a combustor 3 and a turbine 5 . As is known, the incoming air is compressed by compressor 2 and then enters the plenum defined by the casing of the gas turbine ( figure 1 not shown in ). Compressed air enters the burner stage from the plenum. In the burner stage, air is ...

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Abstract

A gas turbine for a power plant, the gas turbine (1) comprising a compressor stage (2), a burner stage (3) provided with a plurality of can burners (4), at least one turbine stage (5) and An outer casing (6) defining a plenum (20) and provided with a plurality of inlet holes (7) for supporting the can burner (4); each inlet hole (7) includes an inner surface (13) , said inner surface (13) faces and is spaced apart from the associated can combustor (4) so ​​as to realize a gap (9) to allow compressed air to flow from the air chamber (20) into the combustor can (4); wherein At each inlet hole (7), the gas turbine (1) comprises thermal management means configured for applying at least a heat treatment to the inner surface (13) of the associated inlet hole (7).

Description

[0001] priority statement [0002] This application claims priority from European Patent Application No. 17175152.2 filed on June 9, 2017, the disclosure of which is incorporated herein by reference. technical field [0003] The invention relates to a gas turbine for a power plant comprising a plurality of can combustors. In particular, the invention relates to the interaction between each can combustor and the associated inlet aperture provided by the casing of the gas turbine. Background technique [0004] As is known, a gas turbine for a power plant (hereinafter simply gas turbine) comprises a rotor provided with an upstream compressor section, a combustor section and a downstream turbine section. The terms downstream and upstream refer to the direction of the main gas flow through the gas turbine. Specifically, the compressor section includes an air-supplied inlet and a plurality of vanes connected to the rotor and configured to compress the incoming air. Compressed ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/00F23R3/14
CPCF23R3/005F23R3/14F01D9/023F23R3/002F23R3/283F23R3/46F23R2900/03044F02C7/18
Inventor J.安桂索拉麦菲特O.泰恩尼T.C.胡贝N.布哈特纳格M.克拉迪D.优格尔
Owner ANSALDO ENERGIA SWITZERLAND AG