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
CN107178792AInactive Publication Date: 2017-09-19DONGFANG TURBINE CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
DONGFANG TURBINE CO LTD
Publication Date
2017-09-19
Estimated Expiration
Not applicable · inactive patent

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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.
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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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