turbine engine combustor
A turbine engine and combustion chamber technology, which is applied in the combustion chamber, continuous combustion chamber, combustion method and other directions, can solve the problem that the ignition and cross-flame requirements of the combustion chamber with large diameter and small hair cannot be satisfied, and the length of the engine shaft and the diameter of the combustion chamber can be shortened. To solve problems such as size increase, the effect of weight reduction, structure simplification and cost reduction can be achieved.
Active Publication Date: 2022-03-25
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0004] However, the turbine of the tip turbofan engine is directly connected to the compressor, and the combustion chamber is placed outside the engine, which obviously shortens the shafting length of the engine
However, since the combustion chamber is placed outside the engine, the radial size of the combustion chamber is significantly increased, and the existing structural layout of the combustion chamber cannot meet the requirements of large-diameter and small-engine combustion chambers for ignition and cross-fire
Method used
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[0029] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments, however, can be embodied in various forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.
[0030] Although relative terms such as "upper" and "lower" are used in this specification to describe the relative relationship of one component of an icon to another component, these terms are used in this specification only for convenience, such as according to the direction of the example described. It will be appreciated that if the device of the icon is turned upside down, the components described as "on" will become ...
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The present disclosure relates to a turbine engine combustor. The combustion chamber includes a flame tube, a diffuser and a plurality of nozzles, the flame tube includes an outer ring of the flame tube, an inner ring of the flame tube and a head of the flame tube, and the outer ring of the flame tube and the inner ring of the flame tube form an annular airflow chamber, The head of the flame tube includes a plurality of air inlet heads that are distributed in a ring and protrude along the axial direction of the flame tube; the diffuser includes guide vanes, which can make the air flow at the outlet of the diffuser follow the direction of the outlet of the diffuser Circumferential rotation of the diffuser, the outlet of the diffuser is opposite to the direction of the gas flow in the gas flow cavity; multiple nozzles are distributed on the outer ring of the flame tube along the axial circumferential direction of the flame tube, and communicate with the gas flow cavity; A plurality of oblique holes are provided, and the inclination direction of the oblique holes is consistent with the deflection direction of the guide vanes; the outer ring of the flame tube is provided with a plurality of main combustion holes in the outer ring along the circumference, and the inner ring of the flame tube is provided with a plurality of inner Ring main combustion hole.
Description
technical field [0001] The present disclosure relates to the technical field of turbine engines, and in particular, to a turbine engine combustion chamber. Background technique [0002] With the rapid development of aviation technology and the improvement of user needs, people have put forward higher requirements for turbine engines, and some new configurations of turbine engines have also appeared one after another, such as tip turbofan engines. [0003] As one of the three major components of a turbine engine, the combustion chamber is usually located between the compressor and the turbine. It is used to convert the chemical energy in the fuel into heat energy and heat the high-pressure air after the compressor is supercharged to the allowable temperature before the turbine. , so as to enter the exhaust device to expand and do work. [0004] However, the turbine of the tip turbofan engine is directly connected to the compressor, and the combustion chamber is placed outsid...
Claims
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IPC IPC(8): F23R3/28F23R3/38
CPCF23R3/286F23R3/38
Inventor 邬俊江立军陈敏敏陈翔汤姣
Owner AECC HUNAN AVIATION POWERPLANT RES INST