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Gas turbine

A technology of gas turbines and turbines, which is applied in the direction of gas turbine devices, combustion chambers, combustion methods, etc., and can solve problems such as impact, extra cost, and reduced lifespan

Active Publication Date: 2014-12-24
GENERAL ELECTRIC TECH GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, it also affects or reduces the life expectancy
Last but not least, additional costs in readjusting the machine can be expected

Method used

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Embodiment Construction

[0041] In the transition region A described at the beginning, the inner combustion chamber casing 20a with its cooling jacket 19a and the turbine inlet ( Figure 4 The transition between the inner walls in 26) is now designed in such a way that it allows and withstands relative movements caused by thermal expansion. The space between the two components is flow-technically defined by a plate-shaped transition element ( Figure 4 30) in the bridge, which on the one hand is pivotally supported at the inner combustion chamber housing 20a and on the other hand passes through a pressure spring at its free end ( Figure 4 28) Loaded compression bolts ( Figure 4 27) in the inner wall of the turbine inlet 26 is pressed against the outside of the turbine inlet 26, that is, it can move transversely to the axis of the pressing bolt 27. In this way, a sealed transition between the combustion chamber and the turbine inlet is achieved for the hot gases, which allows and compensates for a ...

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PUM

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Abstract

A gas turbine (10) comprises a compressor (12), an annular combustion chamber (13), and a turbine (15), a combustion chamber shell (20a) of the combustion chamber (13) adjoining the turbine inlet (26) in a transition region (A) in order to introduce the hot gases generated in the combustion chamber (13) into the downstream turbine (15) such that a thermal expansion-induced relative movement between the combustion chamber (13) and the turbine inlet (26) is possible. Combustion chamber shell (20a) support elements (29) distributed on the periphery come into contact with a conical contour (31a) on the shaft cover (25) due to the thermal expansion (33) that occurs during operation and are supported on said contour. The aim of the invention is an improvement with respect to loading and service life. This is achieved in that the conical contour (31a) and the machine axis form an angle (alpha2) that allows the combustion chamber shell (20a) support elements (29) to slide onto the conical contour (31a).

Description

technical field [0001] The invention relates to the technical field of gas turbines. The invention relates to the transition region between the annular combustion chamber and the adjoining turbine. Background technique [0002] The invention takes as a starting point a gas turbine which, in the simplest case, has the figure 1 A schematic diagram as described in . figure 1 The gas turbine 10 includes a compressor 12 , a combustor 13 and a turbine 15 . The compressor 12 takes in combustion air through the air inlet 11 and compresses the combustion air. The compressed air is introduced into the combustion chamber 13 and used there for the combustion of fuel 14 . The resulting hot gas is depressurized in the subsequent turbine 15 with power generation and leaves the turbine 15 as exhaust gas 16 . [0003] Modern (stationary) industrial gas turbines (IGT) are usually designed with an annular or annular combustor. In generally smaller IGTs the combustion chambers are impleme...

Claims

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Application Information

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IPC IPC(8): F23R3/60
CPCF23R3/60F23R2900/00012F02C7/20F01D9/023F01D25/28F23R3/002
Inventor R. 特舒奧S. 纳兰西G. 菲科恩
Owner GENERAL ELECTRIC TECH GMBH