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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 reduced service life, additional costs, and impacts

Active Publication Date: 2016-06-08
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

The gas turbine (10) comprises a compressor (12), an annular combustor (13) and a turbine (15), wherein, in order to introduce hot gases generated in the combustor (13) into the subsequent turbine (15) , the combustor (13) is coupled to the turbine inlet (26) in the transition region (A) using the combustor housing (20a) such that thermal expansion can be achieved between the combustor (13) and the turbine inlet (26) and wherein, due to the thermal expansion (33) that occurs during operation, the combustion chamber casing (20a) adjoins the cone at the shaft cover (25) with support elements (29) installed distributedly at the circumference shape profile (31a) and is supported there. The improvement in terms of load and life is achieved by the fact that the conical profile (31a) encloses an angle (α2) with the machine axis which enables the combustion chamber housing (20a) to slide onto the conical profile (31a) using the support element (29) )superior.

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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Patent Type & Authority Patents(China)
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