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Device for cooling fuel nozzles and aeroengine including same

A technology for fuel nozzles and cooling air, which is applied in combustion chambers, combustion methods, combustion equipment, etc., and can solve the problems of thermal protection technology that cannot meet design requirements, high cost, and complex structure.

Active Publication Date: 2021-09-10
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] The technical problem to be solved by the present invention is to provide a device for cooling fuel nozzles and an aero-engine including the same in order to overcome the disadvantages of the nozzle thermal protection technology for preventing coking that cannot meet the design requirements, complex structure and high cost in the prior art.

Method used

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  • Device for cooling fuel nozzles and aeroengine including same
  • Device for cooling fuel nozzles and aeroengine including same
  • Device for cooling fuel nozzles and aeroengine including same

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Embodiment Construction

[0074] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0075] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same numbers will be used throughout the drawings to refer to the same or like parts.

[0076] In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the description of the present invention may be selected by the applicant according to his or her judgment, and the detailed meanings thereof are set forth herein described in the relevant section of the description. ...

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Abstract

The present invention provides a device for cooling fuel nozzles and an aviation engine that includes its aircraft.Spirit, install it into the burning room, set a nozzle cooling air inlet pipeline, a cooling air exhaust pipe road, and a main combustion -level fuel pipeline inside the nozzle;Connected to the induction unit, the other end of the nozzle cooling air intake pipeline is connected to the main combustion -grade fuel pipeline on the main combustion -level fuel pipeline;The main combustion -level oil collection ring is connected, and the other end is connected with the burning room.Due to the simple protection structure of the nozzle, the nozzle manufacturing cost, and the low temperature of the cooling medium can achieve a better nozzle thermal protection effect and avoid scoring, thereby increasing the nozzle life or maintenance time interval, reducing the cost of use.

Description

technical field [0001] The invention relates to the field of civil aeroengines, in particular to a device for cooling fuel nozzles and an aeroengine comprising the same. Background technique [0002] In the field of aero-engines, with the increasingly stringent environmental protection requirements, the pollution emission restrictions of civil aero-engines are becoming more and more stringent. Contemporary civil aero-engines widely adopt low-emission combustion technology to meet low-emission requirements. [0003] Among low-emission combustion technologies, lean-oil low-emission combustion technology has the greatest potential in reducing emissions, and is a very promising low-emission technology. Lean fuel and low emission technology usually requires the use of graded fuel nozzles. The nozzles are divided into pre-combustion stage and main combustion stage. Under small conditions, only the pre-combustion stage supplies fuel, and under heavy conditions, the pre-combustion s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28
CPCF23R3/28
Inventor 何沛徐康陈毓卿
Owner AECC COMML AIRCRAFT ENGINE CO LTD