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Combustion chamber structure of gas turbine

A gas turbine and combustor technology, which is applied in gas turbine devices, combustors, continuous combustors, etc., can solve problems such as reducing turbine efficiency

Inactive Publication Date: 2006-10-18
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As already explained above, this pressure loss reduces the efficiency of the turbine

Method used

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  • Combustion chamber structure of gas turbine
  • Combustion chamber structure of gas turbine
  • Combustion chamber structure of gas turbine

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Embodiment Construction

[0022] In these figures, the same parts are provided with the same reference numerals.

[0023] figure 1 A partially cutaway perspective view of a combustion chamber arrangement 1 according to the invention is shown. A plurality of separate combustion chambers 2 arranged substantially in the shape of a circle and of cylindrical configuration open into a common annular combustion chamber 3 . The annular combustion chamber 3 has a double-shell housing with an outer shell 8 and an inner shell 6 . The casing of discrete combustion chamber also all has double shell structure, has corresponding inner shell 5 and outer shell 7 (see figure 2 ). In order to operate a gas turbine equipped with a combustor structure 1 according to the invention, an air / fuel mixture is fed into each separate combustor 2 where it is ignited. In a first phase, the combustion then takes place in the individual combustion chambers 2 , but then also continues into the common annular combustion chamber 3 ....

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Abstract

The invention discloses a combustion chamber structure. To develop a combustion chamber structure for gas turbines with openings into a common annular combustion chamber (3) and efficient cooling with convective cooling, while also dispensing as far as possible the use of impingement cooling Discrete combustion chambers (2) configured in a circular shape, the invention proposes that in this type of combustion chamber structure (1), in the transition region leading to the discrete combustion chambers (2), the annular combustion chamber (3) has Periodically undulating and minimum height in the area between adjacent discrete combustion chambers (2).

Description

technical field [0001] The invention relates to a combustor structure for a gas turbine having a plurality of separate combustors projecting into a common annular combustor and arranged in the shape of a circle. The invention also relates to a gas turbine having a combustion chamber structure designed according to the invention. Background technique [0002] Gas turbines are widely used both in power generation and as a device to drive jet aircraft. In a gas turbine, the air / fuel mixture is ignited in the combustion chamber, and the hot gas flow resulting from the combustion expands in the turbine space, where the hot gas flow contacts the structure including the guide vanes and turbine blades and pushes the The blades on the turbine turn, and thus the shaft itself turns. As an example, a generator for generating electricity can now be operated with the rotational energy thus generated. [0003] Since the combustion of the air / fuel mixture leads to very high temperatures,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/00F02C3/14F23R3/46F01D9/02
CPCF01D9/023F23R3/002F05D2260/201Y02T50/60
Inventor 彼得·蒂曼
Owner SIEMENS AG