CN202813440U

CN202813440U - Combustion chamber of small-sized turbine jet engine

Info

Publication number: CN202813440U
Application number: CN 201220282510
Authority: CN
Inventors: 杨辉
Original assignee: BEIJING ZHONGLU HANGXING MECHANICAL POWER TECHNOLOGY Co Ltd
Current assignee: BEIJING ZHONGLU HANGXING MECHANICAL POWER TECHNOLOGY Co Ltd
Priority date: 2012-06-15
Filing date: 2012-06-15
Publication date: 2013-03-20
Anticipated expiration: 2022-06-15

Abstract

The utility model relates to a combustion chamber of a small-sized turbine jet engine, which comprises a combustion chamber casing, a combustion chamber and a work turbine. The combustion chamber is annularly arranged in the combustion chamber casing; the work turbine is arranged on the outer side of the tail part of the combustion chamber in the combustion chamber casing; and the work turbine comprises a diffuser, a connecting oil pipe and an oil spray nozzle, wherein the diffuser is arranged on the inner wall of the combustion chamber casing in front of the combustion chamber , and the oil spray nozzle is arranged at the front part of the outer wall of the combustion chamber. According to the technical proposal, the oil and gas is uniformly mixed, the smoke and carbon deposition is reduced, the flame is blue, the radiation heat is minimized, the structure is simple, the components used are few, the overall weight of an engine is reduced, the combustion of the fuel is complete, so that the stability of the pushing force and the work efficiency of the engine are improved, the air resistance during operation is reduced, the pressure loss in the combustion chamber is reduced, and the arrangement of a venthole on the outer wall of the combustion chamber can effectively protect the outer wall of the combustion chamber through air cooling, so as to ensure longer service life of the combustion chamber.

Description

Small sized turbine jet engine combustion chamber

Technical field

The utility model relates to a kind of jet engine, particularly relates to a kind of small sized turbine jet engine combustion chamber.

Background technology

In the prior art, as shown in Figure 1, the combustion chamber of jet engine mainly contains fuel oil capillary oil pipe, evaporation tube, outer wall of combustion chamber, Inner Wall of Combustion Chamber composition, and is insufficient in existing structure intermediate fuel oil atomizing, thereby caused efficiency of combustion low, and fuel consume is large; Parts many, complex structure in combustion chamber of the prior art can make the condition and range of combustion chamber steady operation narrower, the cooling difficulty of evaporation tube own simultaneously.

Summary of the invention

In view of this, main purpose of the present utility model is, a kind of small sized turbine jet engine combustion chamber is provided, pass through the technical program, adopt fuel nozzle to replace existing fuel oil capillary oil pipe and evaporation tube, changed the local shape of combustion chamber in the prior art, make air-fuel mixture more even, sufficient combustion is stable, has reduced the coefficient of friction of the pressure loss and high velocity air and combustion chamber, has guaranteed the stability of motor power, simple and compact for structure, reduced amount of parts, alleviate on the whole the weight of engine, adopted the punching type of cooling at outer wall of combustion chamber, prolonged the service life of engine.

In order to achieve the above object, the technical solution of the utility model is achieved in that a kind of small sized turbine jet engine combustion chamber, include combustion box, combustion chamber and work turbine, described combustion chamber is that ring-type is arranged in the combustion box, work turbine is arranged on the combustor tail outside in the combustion box, include diffuser, connected pipes and atomizer, described diffuser is arranged on the inwall that is positioned at the place ahead, combustion chamber combustion box, and described atomizer is arranged on the outer wall of combustion chamber front end.

Described atomizer is centrifugal oil atomizer.

Described for the outer wall of combustion chamber front portion of ring-type is circular-arc, the outside that is positioned at the outer wall of combustion chamber rear portion is ramped shaped.

Described outer wall of combustion chamber surface is provided with the air-vent that is connected with Inner Wall of Combustion Chamber.

Beneficial effect after the employing technique scheme is: a kind of small sized turbine jet engine combustion chamber, pass through the technical program, 1. the employing rotarytype injector makes air-fuel mixture even, has avoided the local oil-poor district in primary zone, reduced and smoldered and carbon distribution, it is blue that flame is, and radiations heat energy is few, makes the outer wall of combustion chamber relative temperature lower, simple in structure, used parts are few, the corresponding minimizing of engine overall weight; 2. flameholding, thus the stability of motor power guaranteed; 3. fuel combustion is fully complete, thereby has guaranteed economy and the efficient height of engine, and the combustion gas of completing combustion enters in the air can not bring environmental pollution; 4. the combustor exit temperature meets the requirements, and guarantees intensity and the life-span of turbine; 5. the pressure loss is little; owing to changed the profile of combustion chamber; reduced the air drag in the work; reduced the pressure loss in the combustion chamber, improved thrust and the economy of engine, 6. lengthened service life; the combustion chamber adopts heat-resisting steel sheet and plate to make; by outer wall of combustion chamber passage is set, can effectively reaches the inflation cooling and protect outer wall of combustion chamber, with the service life that guarantees that the combustion chamber is long.

Description of drawings

Fig. 1 is the prior art structural representation.

Fig. 2 is structural representation of the present utility model.

Fig. 3 is overall structure cutaway view in the utility model.

Fig. 4 is external structure schematic diagram in combustion chamber in the utility model.

Fig. 5 is the side view of Fig. 4.

Among the figure, 1 combustion box, 2 combustion chambers, 3 work turbines, 4 diffusers, 5 connected pipes, 6 atomizers, 7 outer wall of combustion chamber, 8 ramped shaped, 9 Inner Wall of Combustion Chambers, 10 air-vents, 11 centrifugal turbines, 12 nozzle rings.

The specific embodiment

Below in conjunction with accompanying drawing specific embodiment in the utility model is described in further detail.

Such as Fig. 2-shown in Figure 5, the small sized turbine jet engine combustion chamber that the utility model relates to, include combustion box 1, combustion chamber 2 and work turbine 3, described combustion chamber 2 is arranged in the combustion box 1 for ring-type, work turbine 3 is arranged on the 2 afterbodys outside, combustion chamber in the combustion box 1, include diffuser 4, connected pipes 5 and atomizer 6, described diffuser 4 is arranged on the inwall that is positioned at combustion chamber 2 the place ahead combustion boxes 1, and described atomizer 6 is arranged on outer wall of combustion chamber 7 front ends.

Described atomizer 6 is centrifugal oil atomizer.

Described for outer wall of combustion chamber 7 front portions of ring-type are circular-arc, the outside that is positioned at outer wall of combustion chamber 7 rear portions is ramped shaped 8.

Described outer wall of combustion chamber 7 surfaces are provided with the air-vent 10 that is connected with Inner Wall of Combustion Chamber 9.

The utility model is when work, enter combustion chamber 2 from refluence and the diffusion of centrifugal turbine 11 gas process diffuser 4 out, gas is divided into two strands in combustion chamber 2, main air is entered in the combustion chamber 2 by outer wall of combustion chamber 7 air-vents 10 anterior and the first half section, and the fuel mix that sprays in the combustion chamber 2 with atomizer 6 forms the primary zone, to obtain large as far as possible flame propagation velocity; Flow between the loop turn that another strand forms in combustion box 1 and between the outer wall of combustion chamber 7, cooling combustion chamber 2, entered in the combustion chamber 2 by the air-vent 10 on the combustion chamber 2 at last, then the air mixed combustion formation dilution zone with after first burst of atomizing flows to work turbine 3 through nozzle ring 12.

The above only is better possible embodiments of the present utility model, is not to limit protection domain of the present utility model.

Claims

1. small sized turbine jet engine combustion chamber, include combustion box, combustion chamber and work turbine, described combustion chamber is that ring-type is arranged in the combustion box, work turbine is arranged on the combustor tail outside in the combustion box, it is characterized in that, include diffuser, connected pipes and atomizer, described diffuser is arranged on the inwall that is positioned at the place ahead, combustion chamber combustion box, and described atomizer is arranged on the outer wall of combustion chamber front end.

2. small sized turbine jet engine according to claim 1 combustion chamber is characterized in that described atomizer is centrifugal oil atomizer.

3. small sized turbine jet engine according to claim 1 combustion chamber is characterized in that described for the outer wall of combustion chamber front portion of ring-type is circular-arc, the outside that is positioned at the outer wall of combustion chamber rear portion is ramped shaped.

4. small sized turbine jet engine according to claim 1 combustion chamber is characterized in that described outer wall of combustion chamber surface is provided with the air-vent that is connected with Inner Wall of Combustion Chamber.