CN214330769U

CN214330769U - Non-turbine gas turbine

Info

Publication number: CN214330769U
Application number: CN202120017654.0U
Authority: CN
Inventors: 葛建芳
Original assignee: Danyang Da Chuangwei Electrical Equipment Co ltd
Current assignee: Danyang Da Chuangwei Electrical Equipment Co ltd
Priority date: 2021-01-06
Filing date: 2021-01-06
Publication date: 2021-10-01
Anticipated expiration: 2031-01-06

Abstract

The utility model discloses a non-turbine gas turbine, which mainly comprises a gas compressor, a rotor and a shell. The rotor is mainly provided with an oil supply pipeline, a centrifugal impeller, a combustion chamber, a flame barrel and a tangential gas nozzle. When the high-pressure gas burner works, the rotor rotates at a high speed, high-pressure air generated by the coaxial gas compressor is sent to the combustion chamber, fuel oil is combusted in the flame barrel by the combustion chamber through the high-pressure air to form high-pressure gas, and the high-pressure gas is ejected from the tangential nozzle at a speed slightly higher than the tangential speed against the rotation direction of the rotor. The gas ejected at high speed forms reaction force to drive the rotor. Besides maintaining the operation of the rotor and the compressor, the rest part of the newly added power can be used as power output, and the engine has higher thermal efficiency under the condition of no turbine.

Description

Non-turbine gas turbine

Technical Field

The application belongs to the technical field of gas turbines, and particularly relates to a non-turbine gas turbine.

Background

The gas turbine is an internal combustion type power machine which takes continuously flowing gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. The invention of the gas turbine promotes the rapid development of human beings in the engine field and the aviation field. However, the turbine in the gas turbine is subjected to high temperature, high pressure, high impact and high centrifugal force, the operating conditions are extremely harsh, and the material of the turbine becomes an important bottleneck in the development of the gas turbine, which limits the improvement of various performance indexes of the gas turbine.

Therefore, a non-turbine gas turbine is in urgent need of research.

SUMMERY OF THE UTILITY MODEL

In view of this, the present application provides a turbine-less gas turbine, which is used to avoid the trouble of poor applicability caused by the turbine transmission adopted by the conventional gas turbine.

In order to solve the technical problem, the utility model discloses a turbine-free gas turbine, which comprises a gas compressor, wherein the gas compressor is provided with a gas guide passage;

the combustion chamber is communicated with the air guide passage and is arranged on the outer side of the air guide passage through a dynamic sealing element;

the flame barrel is communicated with the air guide passage and positioned in the combustion chamber, an air guide gap is formed between the flame barrel and the combustion chamber, and air inlet holes are distributed on the surface of the flame barrel;

the tail part of the flame barrel and the tail part of the combustion chamber extend to form an annular protruding cavity, and a plurality of tangential nozzles which are communicated with the outside are circumferentially distributed on the annular protruding cavity;

the oil supply pipeline is also a shaft of the gas compressor and is provided with an oil injection pipe penetrating into the flame barrel; and

and the driving output shaft is arranged at the rear end of the flame barrel and penetrates through the combustion chamber.

According to the utility model discloses an embodiment, still locate the shell body of combustion chamber including the cover, the shell body exposes tangential spout and drive output shaft to pass through the cooperation of contactless movable sealing spare with drive output shaft.

According to an embodiment of the present invention, a horizontal rib is disposed between the combustion chamber and the flame tube, and also serves as a supporting member of the flame tube.

According to an embodiment of the present invention, the combustion chamber and the flame barrel are surrounded by a plurality of concave reinforcing ribs.

According to the utility model discloses an embodiment, wherein set up double-deck enhancement baffle between above-mentioned flame bucket and the drive output shaft, double-deck enhancement baffle extends in annular protrusion chamber to it has the inlet port also to have above.

According to an embodiment of the present invention, the end of the combustion chamber located in the air guide passage is provided with a centrifugal impeller.

According to the utility model discloses an embodiment, wherein above-mentioned tangential spout tangential setting, and the spout size of tangential spout is gradually big by flame bucket to combustion chamber.

Compared with the prior art, the application can obtain the following technical effects:

high-pressure air is generated by the air compressor and is sent to the combustion chamber, fuel oil is combusted in the flame barrel by the combustion chamber through the high-pressure air to form high-pressure fuel gas, the high-pressure fuel gas is ejected from the tangential nozzle at a speed slightly higher than the tangential speed against the rotating direction of the rotor (the combustion chamber and the flame barrel), the high-speed ejected fuel gas forms reaction force to enable the rotor to obtain stronger power, and the engine has higher thermal efficiency under the condition of no turbine.

Of course, it is not necessary for any one product to achieve all of the above-described technical effects simultaneously.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:

FIG. 1 is a schematic illustration of a non-turbine gas turbine engine in accordance with an embodiment of the present application;

FIG. 2 is a schematic view of FIG. 1 taken in the direction A;

fig. 3 is a schematic view of fig. 1 in the direction B.

Reference numerals

The device comprises a compressor 10, an air guide passage 20, a combustion chamber 30, a dynamic sealing element 40, a flame barrel 50, a concave reinforcing rib 51, a double-layer reinforcing partition plate 52, a transverse reinforcing rib 53, an air inlet hole 60, a tangential nozzle 70, an oil supply pipeline 80, an oil injection pipe 81, a driving output shaft 90, a non-contact dynamic sealing element 91, an outer shell 100 and a centrifugal impeller 110.

Detailed Description

Embodiments of the present application will be described in detail with reference to the drawings and examples, so that how to implement technical means to solve technical problems and achieve technical effects of the present application can be fully understood and implemented.

Referring to fig. 1-3 together, fig. 1 is a schematic view of a non-turbine gas turbine according to an embodiment of the present application; FIG. 2 is a schematic view of FIG. 1 taken in the direction A; fig. 3 is a schematic view of fig. 1 in the direction B. As shown in the drawing, a non-turbine gas turbine includes a compressor 10, the compressor 10 having an air guide passage 20; a combustion chamber 30 communicating with the air guide passage 20, the combustion chamber 30 being mounted on the outside of the air guide passage 20 via a dynamic seal 40; the flame barrel 50 is communicated with the air guide passage 20 and is positioned in the combustion chamber 30, an air guide gap is formed between the flame barrel 50 and the combustion chamber 30, and an air inlet 60 is distributed on the surface of the flame barrel 50; wherein, the tail part of the flame barrel 50 and the tail part of the combustion chamber 30 extend to form an annular protruding cavity, and a plurality of tangential nozzles 70 which are communicated with the outside are circumferentially distributed on the annular protruding cavity; an oil supply pipeline 80 arranged at the front end of the flame barrel 50, wherein the oil supply pipeline 80 is also a shaft of the compressor 10 and is provided with an oil injection pipe 81 penetrating into the flame barrel 50; and a driving output shaft 90 disposed at a rear end of the flame barrel 50, the driving output shaft 90 penetrating the combustion chamber 30.

In one embodiment of the present invention, the combustion chamber 30 is designed as a hollow cylinder with an axis as a center line, the flame barrel 50 corresponds to the combustion chamber, and the oil supply pipeline 80, the combustion chamber 30, the flame barrel 50, the tangential nozzle 70, and the driving output shaft 90 form a rotor.

In detail, in operation, the compressor 10 completes the intake of high-pressure air through the air guide passage 20, and then guides the high-pressure air into the air guide gap between the combustion chamber 30 and the flame basket 50, and finally enters the interior of the flame basket 30 through the air inlet hole 60. Meanwhile, the fuel supply pipe 80 supplies fuel through a tip nozzle of the fuel injection pipe 81, is introduced into the interior of the flame barrel 50, is mixed with high-pressure air introduced through the air inlet holes 60 to generate combustion, forms high-pressure fuel gas, and is injected at a velocity slightly greater than a tangential velocity through the tangential nozzle holes 70 against a rotation direction of the rotor at the rear of the rotor. At this time, the gas ejected at a high speed forms a reaction force, and the rotor receives a stronger power, and the power is finally transmitted through the drive output shaft 90. It is worth mentioning that the newly added power is used as power output in addition to maintaining the operation of the rotor and the compressor 10, so that the engine has higher thermal efficiency without a turbine.

In addition, the high pressure air entering through the intake holes 60 has a smaller rotation radius, and the rotation speed thereof is also increased, thereby facilitating disturbance of the internal gas, and thus facilitating sufficient mixing and combustion of fuel and air.

The utility model discloses still locate combustion chamber 30's shell body 100 including the cover, shell body 100 exposes tangential spout 70 and drive output shaft 90 to with drive output shaft 90 through contactless movable sealing element 91 cooperation. In the present embodiment, the outer casing 100 wraps the rotor while leaving a certain gap with the rotor, and the gap is evacuated due to the high-speed rotation of the rotor and the injection of the high-speed airflow at the nozzle, so as to reduce the friction resistance between the rotor and the air, and the front part of the outer casing is connected to the non-rotating part of the engine, and the rear part of the outer casing is connected to the driving output shaft 90 through the non-contact rotating seal 91. In addition, the position where the tangential nozzle 70 is exposed is provided with an exhaust port to form an exhaust passage, thereby completing the exhaust.

In a preferred embodiment, a lateral rib 53 is provided between the combustion chamber 30 and the flame basket 50, and also serves as a support member for the flame basket 50.

The combustion chamber 30 and the flame barrel 50 are annularly provided with a plurality of sections of concave reinforcing ribs 51 for enhancing the strength of the rotor and improving the application range.

In a similar way, a double-layer reinforcing partition plate 52 is arranged between the flame barrel 50 and the drive output shaft 90, the double-layer reinforcing partition plate 52 extends to the annular protruding cavity, and air inlet holes 60 are distributed in the double-layer reinforcing partition plate, so that the connection with the drive output shaft 90 is reinforced, and the stabilizing effect is improved.

Additionally, the utility model discloses a tip that combustion chamber 30 is located air guide passageway 20 is equipped with centrifugal impeller 110, can further compress the highly-compressed air that compressor 10 conveyed and come and improve pressure, and highly-compressed air after the pressurization is advanced to be gone into the air guide clearance, and the inlet port 60 through combustion chamber 30 respectively gets into flame bucket 50 again, improves the rotation efficiency of rotor.

The tangential nozzle 70 of the utility model is tangentially arranged, and the nozzle size of the tangential nozzle 70 is gradually enlarged from the flame barrel 50 to the combustion chamber 30. When the rotor rotates at high speed, the linear velocity of the rotor at the tangential nozzle 70 is high, and if the tangential nozzle 70 jets air reversely outwards at high speed, the efficiency of the jet propulsion is high. If the exhaust speed and the nozzle linear speed are designed accurately, the difference between the exhaust speed and the nozzle linear speed is as small as possible, the absolute speed of the exhaust gas can be quite small, and the kinetic energy taken away is little, so that the energy conversion rate is greatly improved, and the engine has higher thermal efficiency under the condition of no turbine.

To sum up, the utility model discloses the during operation rotor is high-speed rotatory, the highly-compressed air that coaxial compressor produced is sent to the combustion chamber, the combustion chamber utilizes highly-compressed air to burn the fuel in the flame bucket, form high-pressure gas, high-pressure gas is blown out from the tangential spout against rotor direction of rotation, high-speed spun gas forms reaction force and lets the rotor obtain power, and newly-increased power is except maintaining rotor and compressor operation, all the other parts can regard as power output, finally through the jet-propelled conversion power of rotor tangential, traditional turbine has been saved, the thermal efficiency also can be higher.

The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.

Claims

1. A non-turbine gas turbine engine, comprising:

the air compressor is provided with an air guide passage;

the flame barrel is communicated with the air guide passage and is positioned in the combustion chamber, an air guide gap is formed between the flame barrel and the combustion chamber, and air inlet holes are distributed on the surface of the flame barrel;

the oil supply pipeline is arranged at the front end of the flame barrel, is also a shaft of the compressor and is provided with an oil injection pipe penetrating into the flame barrel; and

2. The non-turbine gas turbine engine of claim 1, further comprising an outer casing surrounding said combustion chamber, said outer casing exposing said tangential nozzle and said drive output shaft and engaging said drive output shaft through a non-contact dynamic seal.

3. The non-turbine gas turbine according to claim 1, wherein a transverse stiffener is provided between the combustion chamber and the flame barrel.

4. The non-turbine gas turbine according to claim 1, wherein the combustion chamber and the flame barrel are surrounded by a plurality of recessed ribs.

5. The non-turbine gas turbine according to claim 1, wherein a double-layer reinforcing partition is provided between the flame barrel and the drive output shaft, the double-layer reinforcing partition extending in the annular projecting cavity and having the air inlet holes distributed thereon.

6. The non-turbine gas turbine according to claim 1, wherein the end of the combustion chamber located in the air guide passage is provided with a centrifugal impeller.

7. The non-turbine gas turbine according to claim 1, wherein the tangential ports are arranged tangentially, and a port size of the tangential ports increases from the flame barrel to the combustor.