CN211976933U

CN211976933U - Combustor based on turbine engine

Info

Publication number: CN211976933U
Application number: CN201920690367.9U
Authority: CN
Inventors: 徐子然
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-05-13
Filing date: 2019-05-13
Publication date: 2020-11-20
Anticipated expiration: 2029-05-13

Abstract

The utility model relates to a combustor based on turbine engine, include: a support housing defining an interior volume such that a combustion space is formed within the housing; a fuel nozzle group including a plurality of fuel nozzles provided at a front end of the support housing; an annular liner forming a flow path with the support housing directing a flow of air from an annulus between the annular liner and the support housing through the air inlet radially inward into the combustion space; a plurality of guide vane sets up in flow path, and both sides paste with support shell and annular inside lining respectively mutually, and guide vane has corresponding angle with the axis of worm wheel combustor, and a plurality of guide vane form spiral guide vane group, and the guide vane middle part is located the clitellum position, and forms heat guide vane to the inside radial protrusion of combustion space. The utility model provides a turbine engine's that is heated and cools off evenly combustor.

Description

Combustor based on turbine engine

Technical Field

The utility model belongs to the technical field of turbine engine and specifically relates to a combustor based on turbine engine.

Background

Gas turbine engines combust a mixture of fuel and air to produce hot combustion gases that drive one or more turbine stages. Specifically, the hot combustion gases force the turbine blades to rotate, thereby driving the shaft to rotate one or more loads. Typically, combustion occurs within a combustion chamber formed by a combustion liner disposed within a flow sleeve. Thus, the combustion liner is heated by the combustion reaction. Thermal gradients caused by combustion may cause uneven heat distribution in the combustion liner, resulting in hot streaks and temperature gradients, which may make the heat distribution of the combustion liner more uneven if impingement cooling is used, which may shorten the useful life of the part material.

Disclosure of Invention

The utility model provides an overcome the problem that exists among the above-mentioned, provide a be heated and cool off even turbine engine's combustor.

The utility model provides a technical scheme that its technical problem adopted is: a turbine engine-based combustor comprising: a support housing defining an interior volume such that a combustion space is formed within the housing;

a fuel nozzle group including a plurality of fuel nozzles provided at a front end of the support housing;

an annular liner forming a flow path with the support housing directing a flow of air from an annulus between the annular liner and the support housing through the air inlet radially inward into the combustion space;

a plurality of guide vane sets up in flow path, and both sides paste with support shell and annular inside lining respectively mutually, and guide vane has corresponding angle with the axis of worm wheel combustor, and a plurality of guide vane form spiral guide vane group, and the guide vane middle part is located the clitellum position, and forms heat guide vane to the inside radial protrusion of combustion space.

Preferably, the annular lining is made of graphene titanium alloy material.

Preferably, the guide vane has an angle of 5 to 20 degrees with the axis of the worm wheel burner.

Preferably, the guide vanes have a curved curvature.

Preferably, the plurality of heat conducting blades are surrounded in a ring belt.

Preferably, the flow path communicates with a forward end of the fuel nozzle, and at least a portion of the air is directed from the flow path into the forward end of the fuel nozzle.

The utility model has the advantages that: a combustor based on a turbine engine is characterized in that hot flow forms rotation through a heat guide vane, so that the guide is smooth, and the heat distribution is uniform; as the air passes through the flow path, it circulates with the path angle of the guide vanes, the path before entering the annulus increases, and the guidance is smooth, increasing the amount of time for heat transfer between the air and the annular liner via convection, thereby making its cooling more uniform.

Drawings

The present invention will be further explained with reference to the drawings and examples.

FIG. 1 is a schematic view of an overall structure of a combustor based on a turbine engine according to the present invention;

fig. 2 is a schematic structural view of a guide vane of a combustor based on a turbine engine according to the present invention.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic drawings and illustrate the basic structure of the present invention only in a schematic manner, and thus show only the components related to the present invention.

Example 1

A turbine engine based combustor as shown in fig. 1, 2, comprising: a support housing 1 defining an internal volume such that a combustion space 2 is formed inside the housing;

a fuel nozzle group 3 including a plurality of fuel nozzles provided at the front end of the support casing 1;

an annular liner 4 forming a flow path 5 with the support housing 1, directing a flow of air from an annulus 6 between the annular liner 4 and the support housing 1 through an air inlet radially inwardly into the combustion space 2;

the guide vanes 7 are arranged in the flow path 5, two sides of the guide vanes 7 are respectively attached to the support shell 1 and the annular lining 4, the guide vanes 7 and the axis of the worm gear combustor have corresponding angles, the guide vanes 7 form a spiral guide vane group, the middle parts of the guide vanes are positioned at the position of the annular belt 6, and the guide vanes radially protrude towards the inside of the combustion space 2 to form heat guide vanes 71.

Wherein, the heat flow forms a rotation through the heat guide vane 71, the guiding is smooth, and the heat distribution is uniform; as the air passes through flow path 5, it circulates with the path angle of guide vanes 7, the path before entering annulus 6 increases and the guidance is smooth, increasing the amount of time for heat transfer between the air and annular liner 4 via convection, thereby making its cooling more uniform.

The annular lining 4 is made of graphene titanium alloy material. The titanium alloy has high strength, good corrosion resistance and high heat resistance, and after the graphene is mixed, the performance of the annular lining 4 is further improved, and the service life is prolonged.

The angle between the guide vane 7 and the axis of the worm gear combustor is 5-20 degrees. In the present embodiment, 15 degrees is used, so that the swirling air can be generated, the time of the swirling air in the flow path 5 is increased, the heat transfer is sufficiently and uniformly performed, and the cooling is more uniform.

The guide vanes 7 have a curved curvature. Further increasing the time of the swirling air in the flow path 5.

The plurality of heat conducting vanes 71 are surrounded in the annulus 6 and project radially inwardly of the combustion space 2.

The flow path 5 is connected to the front end of the fuel nozzle, and at least part of the air is guided into the front end of the fuel nozzle through the flow path 5. The heat flow is swirled to ignite the fuel mixture and the combustion gases are discharged to the turbine.

In the combustor based on the turbine engine, the hot flow forms rotation through the hot flow guide blades, the guiding is smooth, and the heat distribution is uniform; as the air passes through the flow path, it circulates with the path angle of the guide vanes, the path before entering the annulus increases, and the guidance is smooth, increasing the amount of time for heat transfer between the air and the annular liner via convection, thereby making its cooling more uniform.

In light of the foregoing, it will be apparent to those skilled in the art from this disclosure that various changes and modifications can be made without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.

Claims

1. A turbine engine based combustor, comprising: a support housing defining an interior volume such that a combustion space is formed within the housing;

2. The turbine engine-based combustor of claim 1, wherein: the annular lining is made of graphene titanium alloy material.

3. The turbine engine-based combustor of claim 1, wherein: the angle between the guide vane and the axis of the worm gear combustor is 5-20 degrees.

4. A turbine engine based combustor according to claim 3, wherein: the guide vanes have a curved arc.

5. The turbine engine-based combustor of claim 1, wherein: the plurality of heat conduction flow blades are surrounded in the ring band.

6. The turbine engine-based combustor of claim 1, wherein: the flow path communicates to a forward end of the fuel nozzle, and at least a portion of the air is directed from the flow path into the forward end of the fuel nozzle.