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Gas turbine and aircraft engine combustor tail cylinder structure

A technology for aero-engines and gas turbines, applied in the directions of combustion chambers, combustion methods, combustion equipment, etc., can solve problems such as high price, achieve the effect of simple molding and reduce manufacturing costs

Inactive Publication Date: 2017-09-19
DONGFANG TURBINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the selection of advanced gas turbine (aero engine) combustor tailpipe is the most advanced superalloy material in the world, and the price is very expensive.

Method used

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  • Gas turbine and aircraft engine combustor tail cylinder structure
  • Gas turbine and aircraft engine combustor tail cylinder structure
  • Gas turbine and aircraft engine combustor tail cylinder structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0019] Such as Figure 1 to Figure 3 Shown: a gas turbine and aero-engine combustor transition piece 1 structure, including a support ring 2, a transition piece body 3 and an outlet flange 4; the support ring 2 is installed on the front end of the transition piece body 3; the outlet The flange 4 is installed at the rear end of the tailpiece body 3; the tailpiece body 3 is welded by six sections of superalloys with different high temperature resistance properties; and according to the distribution trend of the metal temperature, the part with higher temperature is the resistant The material with high high temperature performance, the part with lower temperature is the material with poor high temperature resistance. Six sections of high-temperature alloys with different high-temperature resistance properties are welded to form a complete transition tube body 3 as a whole. The superalloys of the six stages with different high temperature resistance properties are arranged in asc...

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Abstract

The invention discloses a gas turbine and aircraft engine combustor tail cylinder structure. The structure comprises a support ring, a tail cylinder body and an outlet flange; the support ring is mounted at the front end of the tail cylinder body; and the outlet flange is mounted at the back end of the tail cylinder body. The structure is characterized in that the tail cylinder body is formed by connecting multiple sections of high-temperature alloys with different high-temperature resisting performances; and according to the metal temperature distribution tendency, the part with higher temperature is a material with higher high-temperature resisting performance, and the part with lower temperature is a material with weaker high-temperature resisting performance. The structure not only can exert the mechanical performances of the materials to the greatest extent, but also can greatly reduce the tail cylinder production cost, and in particular, is suitable for design of traditional gas turbine (aircraft engine) combustor tail cylinders with higher temperature.

Description

technical field [0001] The invention relates to the technical field of gas turbines (aeroengines), in particular to a gas turbine (aeroengine) combustor transition structure. Background technique [0002] Gas turbine (aero engine) burner is a kind of combustion equipment made of high temperature resistant alloy material, which is one of the essential components in gas turbine (aero engine). The fuel converts chemical energy into thermal energy through combustion chemical reaction in the combustor, forming high-temperature and high-pressure combustion products, and driving the turbine (turbine) to do work. The tailpiece of the burner is connected to the flame tube of the burner and the turbine, and the temperature of the passing gas is as high as 1400K~2000K. [0003] The inside of the tail piece of the burner is a high-temperature gas channel, and the outside is impinged by cooling air to achieve the purpose of cooling. Therefore, the metal temperature of the transition pi...

Claims

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Application Information

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IPC IPC(8): F23R3/00
CPCF23R3/002
Inventor 赵仕志刘维兵成露范小平艾松张晓东周洪宇孙奇赵世全陈贝贝章艳陈晓平饶真炎
Owner DONGFANG TURBINE CO LTD
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