CN212003270U

CN212003270U - Turbine engine

Info

Publication number: CN212003270U
Application number: CN202020208817.9U
Authority: CN
Inventors: 周磊; 张晓东
Original assignee: Zhuhai Heze Technology Co ltd
Current assignee: Zhuhai Heze Technology Co ltd
Priority date: 2020-02-25
Filing date: 2020-02-25
Publication date: 2020-11-24
Anticipated expiration: 2030-02-25

Abstract

The utility model discloses a turbine engine, which comprises a shell, a turbine rotor, a combustor and a bearing seat; the turbine rotor comprises a turbine shaft, a turbine disc and a plurality of blades, the outer edge of the blade tip of each blade is provided with at least two openings with gradually increasing openings, and the inside of each blade is provided with a ventilation cavity; the combustor comprises an outer barrel part, an inner barrel part, a roof and a conical disc, wherein the outer barrel part, the inner barrel part, the roof and the conical disc enclose a combustion chamber, a plurality of fuel inlet holes are formed in the conical disc, and an evaporation pipe is arranged in the combustion chamber corresponding to each fuel inlet hole. The blade is provided with a cavity and a notch with specific functions, and the weight of the blade is reduced; in addition, the evaporation tube is arranged corresponding to the fuel inlet hole, so that the atomization effect of the fuel can be improved, and the combustion effect can be improved; the thrust performance of the engine is improved from multiple aspects.

Description

Turbine engine

Technical Field

The utility model relates to an engine field, especially a turbine engine.

Background

The turbine engine depends on combustion gas to generate thrust, air is sucked from the atmosphere, the air obtains energy and momentum after compression and heating processes, the air with the energy and the momentum is discharged from a thrust nozzle, and when high-speed gas is sprayed out of the engine, the turbine is driven to continuously rotate to maintain a working cycle. The thrust performance of a turbine engine is closely related to the components and assembly relationship thereof. The existing turbine engine has a plurality of defects influencing the thrust performance, such as insufficient combustion and low efficiency of a combustor, heavy mass of an impeller and overhigh temperature during working

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve one of the technical problem that exists among the prior art at least, provide a turbine engine, be favorable to promoting thrust performance.

The utility model provides a technical scheme that its problem adopted is:

a turbine engine comprising a casing, a turbine rotor, a combustor and a bearing housing; the turbine rotor comprises a turbine shaft arranged on the bearing seat, a turbine disc arranged on the turbine shaft and a plurality of blades arranged on the peripheral edge of the turbine disc, the outer edge of the blade tip of each blade is provided with at least two openings with gradually increased openings for judging the abrasion loss of the blade tip, and a ventilation cavity is arranged inside each blade; the combustor comprises an outer barrel component, an inner barrel component, a roof and a conical disc, the outer barrel component, the inner barrel component, the roof and the conical disc enclose a combustion chamber, a plurality of fuel oil inlet holes are formed in the conical disc, and evaporation tubes are arranged in the combustion chamber corresponding to each fuel oil inlet hole.

The turbine engine has at least the following beneficial effects: the blade is internally provided with a ventilation cavity for introducing cold air to cool the surface temperature of the blade, the outer edge of the blade tip of the blade is provided with a notch for judging the abrasion loss of the blade tip, and the cavity and the notch have specific functions and are beneficial to reducing the weight of the blade; in addition, the evaporation tube is arranged corresponding to the fuel inlet hole, so that the atomization effect of the fuel can be improved, and the combustion effect can be improved; the thrust performance of the engine is improved from multiple aspects.

Furthermore, the outer ring surface of the turbine disc is provided with a plurality of tenons, and the blade root of each blade is provided with a mortise matched with the tenons.

Further, the chamber top is provided with a plurality of air inlet holes.

Further, the evaporation tube extends in the axial direction of the inner tube member.

Specifically, four fuel inlet holes are formed, and are evenly distributed along the circumferential direction of the conical disc; the number of the corresponding evaporation tubes is four.

Specifically, the inner diameter of each evaporation tube was 8 mm.

Specifically, there are three of the gaps.

Furthermore, the end face of the turbine shaft is provided with a blind hole extending along the length direction of the turbine shaft.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The invention is further described with reference to the following figures and examples.

FIG. 1 is a block diagram of a turbine engine according to an embodiment of the present invention;

FIG. 2 is a block diagram of the turbine rotor of FIG. 1;

FIG. 3 is a block diagram of the burner of FIG. 1;

FIG. 4 is a block diagram of the blade of FIG. 2.

Detailed Description

This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1 to 4, an embodiment of the present invention provides a turbine engine including a casing 100, a turbine rotor 300, a combustor 400, and a bearing housing 200; the turbine rotor 300 comprises a turbine shaft 310 mounted on the bearing seat 200, a turbine disc 320 arranged on the turbine shaft 310 and a plurality of blades 330 arranged on the peripheral edge of the turbine disc 320, the outer edge of the blade tip of each blade 330 is provided with at least two openings 332 with gradually increasing openings for judging the abrasion loss of the blade tip, and the blades 330 are internally provided with ventilation cavities 331; the combustor 400 comprises an outer cylinder component 410, an inner cylinder component 420, a roof 430 and a conical disc 440, wherein the outer cylinder component 410, the inner cylinder component 420, the roof 430 and the conical disc 440 enclose a combustion chamber, a plurality of fuel inlet holes are formed in the conical disc 440, and an evaporation pipe 450 is arranged in the combustion chamber corresponding to each fuel inlet hole.

In this embodiment, a ventilation cavity 331 is disposed inside the blade 330 for introducing cool air to cool the surface temperature of the blade 330, and a notch 332 is disposed at the outer edge of the blade tip of the blade 330, and the ventilation cavity 331 and the notch 332 not only have specific functions, but also are beneficial to reducing the weight of the blade 330. In addition, the fuel injected from the fuel injection pipe is atomized in the preheated evaporation pipe 450, and the atomized fuel enters the combustion chamber from the evaporation pipe 450 to be mixed with air in the combustion chamber and then is combusted, so that high-temperature and high-pressure gas is generated. The evaporation tube 450 is arranged corresponding to the fuel inlet hole, so that the atomization effect of the fuel can be improved, and the combustion effect can be improved. The thrust performance of the engine is improved from multiple aspects.

Referring to fig. 4, the ventilation cavity 331 facilitates the introduction of cool air to cool the surface of the vane 330. The cool air flows through the hollow ducts of the turbine shaft 310 and the hollow ducts of the turbine disk 320 into the breather cavity 331, cooling the blades 330. The blade 330 is easy to wear in the using process, especially the position of the blade tip, through arranging the notches 332, and gradually changing the plurality of notches 332 from small to large, the wear extent of the blade tip can be easily judged and obtained through comparison with the standard notches.

Referring to fig. 2, further, the outer annular surface of the turbine disc 320 is provided with a plurality of tenons 321, and the blade root of the blade 330 is provided with a mortise 333 matched with the tenons 321, so as to facilitate the installation and the removal of the blade 330 and the turbine disc 320.

Specifically, there are three breaks 332. Of course, in other embodiments, the number of gaps 332 may be other than the number of gaps according to the requirements of the application.

Further, a blind hole extending along the length direction of the turbine shaft 310 is provided on the end surface of the turbine shaft 310.

Referring to fig. 3, further, the ceiling 430 is provided with a plurality of intake holes through which external air is introduced into the combustion chamber, so that the air is more sufficiently mixed with the atomized fuel.

Further, the evaporation tube 450 extends in the axial direction of the inner tube member 420, and is attached to the inner tube member 420.

Specifically, four fuel inlet holes are arranged, and the four fuel inlet holes are evenly distributed along the circumferential direction of the conical disc 440; there are four corresponding evaporator tubes 450. Each evaporation tube 450 has an inner diameter of 8 mm. This design is preferred, however, in other embodiments, the number of the evaporation tubes 450 is matched with the number of the fuel inlet holes according to the number of the fuel inlet holes, and the inner diameter of the evaporation tubes 450 may take other values according to actual production requirements.

Above, only the preferred embodiment of the present invention has been described, the present invention is not limited to the above embodiment, and the technical effects of the present invention can be achieved by the same means, which all belong to the protection scope of the present invention.

Claims

1. A turbine engine comprising a housing, a turbine rotor, a combustor and a bearing housing; the turbine rotor comprises a turbine shaft arranged on the bearing seat, a turbine disc arranged on the turbine shaft and a plurality of blades arranged on the peripheral edge of the turbine disc, the outer edge of the blade tip of each blade is provided with at least two openings with gradually increased openings, and a ventilation cavity is arranged inside each blade; the combustor comprises an outer barrel component, an inner barrel component, a roof and a conical disc, the outer barrel component, the inner barrel component, the roof and the conical disc enclose a combustion chamber, a plurality of fuel oil inlet holes are formed in the conical disc, and evaporation tubes are arranged in the combustion chamber corresponding to each fuel oil inlet hole.

2. The turbine engine as claimed in claim 1, wherein the outer annular surface of the turbine disk is provided with a plurality of tenons, and the blade roots of the blades are provided with mortises matching the tenons.

3. A turbine engine in accordance with claim 1, wherein said dome is provided with a plurality of intake apertures.

4. A turbine engine in accordance with claim 3, wherein said evaporator tube extends in the direction of the axis of said inner barrel member.

5. The turbine engine as claimed in claim 4, wherein four fuel inlet holes are provided, and four fuel inlet holes are evenly distributed along the circumferential direction of the conical disc; the number of the corresponding evaporation tubes is four.

6. A turbine engine according to claim 5, wherein the internal diameter of each evaporator tube is 8 mm.

7. A turbine engine in accordance with claim 1, wherein there are three of said breaks.

8. The turbine engine as claimed in claim 1, wherein the turbine shaft has a blind hole in its end face extending in the direction of the length of the turbine shaft.