CN219840726U

CN219840726U - High-rotation-speed aviation turbine engine

Info

Publication number: CN219840726U
Application number: CN202321399150.5U
Authority: CN
Inventors: 申红林; 申原; 陶晶
Original assignee: Nanjing Longpu Power Technology Co ltd
Current assignee: Nanjing Longpu Power Technology Co ltd
Priority date: 2023-06-05
Filing date: 2023-06-05
Publication date: 2023-10-17
Anticipated expiration: 2033-06-05

Abstract

The utility model discloses a high-rotation-speed aviation turbine engine, which relates to the technical field of heat dissipation and comprises an inner shell, wherein a heat dissipation pipe is arranged in the inner shell, an air inlet pipe is arranged on one side of the heat dissipation pipe, and an air outlet pipe is arranged on one side of the heat dissipation pipe away from the air inlet pipe, and the high-rotation-speed aviation turbine engine is characterized by further comprising an outer part: the shell, shell one side is equipped with the air intake, be equipped with the drainage ware in the air intake, be connected with the air-supply line on the air intake, the head end of air-supply line extends to in the air intake to be connected with the drainage ware, the end of air-supply line runs through the shell and extends to in the inner shell to be linked together with the cooling tube, one side that the air intake was kept away from to the shell is equipped with the air outlet, be connected with the tuber pipe on the air outlet, the head end of tuber pipe extends to in the air outlet, the end of tuber pipe runs through the shell and extends to in the inner shell to be linked together with the cooling tube. The utility model cools the radiating fin through external cold air, thereby cooling the high-temperature gas passing through the radiating fin.

Description

High-rotation-speed aviation turbine engine

Technical Field

The utility model relates to the technical field of heat dissipation, in particular to a high-rotation-speed aviation turbine engine.

Background

The turbine supercharged engine is an air compressor, which uses the exhaust gas discharged from the engine as power to drive a turbine in an exhaust passage, and the turbine rotates and drives an impeller coaxially positioned in an air inlet passage, so that the impeller compresses fresh air sent by an air filter pipeline and then sends the fresh air into a cylinder. When the rotation speed of the engine is increased, the high-speed waste gas pushes the turbine to accelerate, the exhaust speed of the waste gas and the rotation speed of the turbine are synchronously increased, the air compression degree is increased, the air inflow of the engine is correspondingly increased, the combustion in the cylinder is more complete, and the power output is higher.

A turbine engine of the retrieved disclosure CN215860499U, comprising a tail spray assembly and a rear bearing cartridge assembly upstream of the tail spray assembly, the tail spray assembly defining a central cone cavity, the rear bearing cartridge assembly defining a rear bearing cavity, the turbine engine further comprising a thermal insulation structure for retarding heat transfer from the central cone cavity to the rear bearing cavity; the heat insulation structure is arranged between the central cone cavity and the rear bearing cavity and separates the central cone cavity from the rear bearing cavity; the heat insulation structure is provided with air holes so that the upstream of the heat insulation structure is communicated with the downstream air circuit of the heat insulation structure, the heat insulation structure comprises a first heat insulation part and a second heat insulation part, the first heat insulation part protrudes from the second heat insulation part in the axial direction, is far away from the rear bearing cavity and is close to the center cone.

When the turbine engine works, air flow is compressed by the air compressor and enters the combustion chamber, the air flow is mixed with fuel in the combustion chamber and combusted, and high-temperature waste gas generated after combustion can damage the shell of the turbine engine for a long time, so that the service life of the turbine engine is reduced.

Disclosure of Invention

The present utility model has been made in view of the above-mentioned problems with existing turbine engines.

Therefore, the utility model aims to provide a high-rotation-speed aviation turbine engine, which solves the problem that high-temperature gas generated in a combustion chamber of the turbine engine can damage a turbine engine shell for a long time when the turbine engine works normally.

In order to achieve the above object, the present utility model provides the following technical solutions:

the utility model provides a high rotational speed aviation turbine engine, includes the inner shell, be equipped with the cooling tube in the inner shell, cooling tube one side is equipped with the air-supply line, one side that the air-supply line was kept away from to the cooling tube is equipped with out the tuber pipe, its characterized in that still includes outside: the air inlet is penetrated and installed with an air inlet pipe, the head end of the air inlet pipe extends into the air inlet and is connected with the air guide device, the tail end of the air inlet pipe penetrates through the outer shell, extends into the inner shell and is communicated with the radiating pipe, the air inlet faces the running direction of the airplane, and cold air outside the airplane is introduced into the air inlet pipe through the air guide device in the air inlet and flows into the radiating pipe through the air inlet pipe.

Preferably, one side of the shell, which is far away from the air inlet, is provided with an air outlet, an air outlet pipe is connected to the air outlet, the head end of the air outlet pipe extends into the air outlet, the tail end of the air outlet pipe penetrates through the shell, extends into the inner shell and is communicated with the radiating pipe, the air outlet is opposite to the running direction of the aircraft, cold air outside the aircraft is prevented from entering the air outlet pipe through the air outlet, and the air outlet can exhaust the cold air heated by the radiating pipe.

Preferably, a rotating shaft is arranged in the inner shell, the rotating shaft and the radiating pipe are in axial symmetry, the rotating shaft penetrates through the central part of the radiating pipe, and the pipe wall of the radiating pipe is tightly attached to the inner shell.

Preferably, the pipe wall of cooling tube is hollow structure, the cooling tube is interior to be distributed with a plurality of fin, the fin is hollow structure and both ends are linked together with the pipe wall of cooling tube, and cold air can even distribute in cooling tube and fin, and the fin has increased the face that contacts with the inside high temperature gas of turbine engine to the efficiency to the high temperature gas cooling has been improved.

Preferably, the plurality of cooling fins are divided into a first plate group and a second plate group, the first plate group and the second plate group are piled up to be arranged in the cooling tube, the distance between the plurality of cooling fins in the first plate group is a first distance, the distance between the first plate group and the second plate group is a second distance, the second distance is larger than the diameter of the rotating shaft, the rotating shaft penetrates through the cooling tube, and friction between the rotating shaft and the cooling fins is avoided when the rotating shaft works normally.

Preferably, one end of the radiating fin, which is close to the air inlet of the turbine engine, is provided with a drainage groove, and the drainage groove is of a conical structure, so that the circulation of gas in the turbine engine is facilitated.

In the technical scheme, the utility model has the technical effects and advantages that:

1. according to the utility model, the radiating pipes are arranged in the inner shell, the two opposite sides of the radiating pipes are respectively connected with the air inlet and the air outlet through the air inlet pipe and the air outlet pipe, the air inlet faces the running direction of the aircraft, the air inlet can introduce cold air outside the aircraft into the radiating pipes to cool the radiating pipes, the air outlet faces away from the running direction of the aircraft, and the air outlet can discharge the heated cold air.

2. According to the utility model, the radiating pipes are internally provided with the plurality of radiating fins, the contact area of the radiating fins with high-temperature gas in the turbine engine is increased, the temperature of the high-temperature gas can be accelerated and reduced, and one ends of the radiating fins are provided with the drainage grooves, so that the circulation of the gas in the turbine engine is facilitated.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings required for the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments described in the present utility model, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.

FIG. 1 is a schematic view of a partial perspective structure of the present utility model;

FIG. 2 is a schematic diagram of the overall structure of the present utility model;

fig. 3 is a schematic view of a partial cross-sectional structure of the present utility model.

Reference numerals illustrate:

1. a housing; 2. an inner case; 3. a rotating shaft; 4. an air inlet; 5. a drainage device; 6. an air inlet pipe; 7. an air outlet pipe; 8. an air outlet; 9. a heat radiating pipe; 10. a heat sink; 11. a first pitch; 12. and a second pitch.

Detailed Description

In order to make the technical scheme of the present utility model better understood by those skilled in the art, the present utility model will be further described in detail with reference to the accompanying drawings.

The embodiment of the utility model discloses a high-rotation-speed aviation turbine engine.

Example 1

Referring to fig. 1 to 3, an embodiment of the present utility model is provided; the utility model provides a high rotational speed aviation turbine engine, includes inner shell 2, is equipped with cooling tube 9 in the inner shell 2, and cooling tube 9 one side is equipped with air-supply line 6, and cooling tube 9 is kept away from one side of air-supply line 6 and is equipped with out tuber pipe 7, its characterized in that still includes outside: the heat radiator comprises an outer shell 1, wherein an air inlet 4 is formed in one side of the outer shell 1, a drainage device 5 is arranged in the air inlet 4, an air inlet pipe 6 is installed in the air inlet 4 in a penetrating mode, the head end of the air inlet pipe 6 extends into the air inlet 4 and is connected with the drainage device 5, the tail end of the air inlet pipe 6 penetrates through the outer shell 1 to extend into an inner shell 2 and is communicated with a heat radiating pipe 9, an air outlet 8 is formed in one side, far away from the air inlet 4, of the outer shell 1, an air outlet pipe 7 is connected to the air outlet 8, the head end of the air outlet pipe 7 extends into the air outlet 8, the tail end of the air outlet pipe 7 penetrates through the outer shell 1 to extend into the inner shell 2 and is communicated with the heat radiating pipe 9, a rotating shaft 3 is arranged in the inner shell 2, the rotating shaft 3 and the heat radiating pipe 9 are in an axisymmetric mode, a plurality of radiating fins 10 are distributed in the heat radiating pipe 9, and two ends of the radiating fins 10 are communicated with the wall of the heat radiating pipe 9.

In this embodiment, when the aircraft is traveling at high altitude and high speed, the air outside the aircraft is cold, the air guide device 5 arranged in the air inlet 4 can guide the cold air outside the aircraft into the air inlet pipe 6, the wall of the radiating pipe 9 is of a hollow structure and is communicated with the air inlet pipe 6, the cold air flows into the radiating pipe 9 from the air inlet pipe 6, a plurality of radiating fins 10 are arranged in the radiating pipe 9, the radiating fins 10 are of a hollow structure and are communicated with the radiating pipe 9 at two ends, and the cold air in the air inlet pipe 9 can be uniformly distributed in the radiating pipe 9 and the radiating fins 10, so that the temperature of the high-temperature air passing through the radiating pipe 9 and the radiating fins 10 is reduced, the air outlet pipe 7 is communicated with the radiating pipe, and the heated cold air can be discharged through the air outlet pipe 7 and the air outlet 8.

Example two

Referring to fig. 1 to 3, an embodiment of the present utility model is provided; compared with embodiment 1, the high-speed aviation turbine engine further comprises: the plurality of cooling fins 10 divide into first board group and second board group, and first board group and second board group symmetry set up in cooling tube 9, and the distance between two adjacent cooling fins 10 in the first board group is first interval 11, and the distance between first board group and the second board group is second interval 12, and second interval 12 is greater than first interval 11, and second interval 12 is greater than the diameter of pivot 3, and the cooling fin 10 is close to turbine engine air inlet's one end and is equipped with the drainage groove, and the drainage groove is the toper structure.

In this embodiment, the rotating shaft 3 passes through the center of the heat dissipating tube 9, so that friction is not generated between the rotating shaft 3 and the heat dissipating fins 10 when the turbine engine is in normal operation, the second space 12 is larger than the diameter of the rotating shaft 3, at least four heat dissipating fins 10 are provided, the heat dissipating fins 10 can increase the contact area with the high temperature gas inside the turbine engine, and a drainage groove is provided at one end of the heat dissipating fins 10 to ensure the normal circulation efficiency of the gas inside the turbine engine.

While certain exemplary embodiments of the present utility model have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that modifications may be made to the described embodiments in various different ways without departing from the spirit and scope of the utility model. Accordingly, the drawings and description are to be regarded as illustrative in nature and not as restrictive of the scope of the utility model, which is defined by the appended claims.

Claims

1. The utility model provides a high rotational speed aviation turbine engine, includes inner shell (2), be equipped with cooling tube (9) in inner shell (2), cooling tube (9) one side is equipped with air-supply line (6), one side that air-supply line (6) was kept away from to cooling tube (9) is equipped with out tuber pipe (7), its characterized in that still includes outside:

the air inlet device comprises an outer shell (1), wherein an air inlet (4) is formed in one side of the outer shell (1), a drainage device (5) is arranged in the air inlet (4), an air inlet pipe (6) is installed in an inserted mode in the air inlet (4), the head end of the air inlet pipe (6) extends into the air inlet (4) and is connected with the drainage device (5), and the tail end of the air inlet pipe (6) penetrates through the outer shell (1) to extend into the inner shell (2) and is communicated with a radiating pipe (9).

2. The high-rotation-speed aeroturbine engine according to claim 1, wherein an air outlet (8) is formed in one side, far away from the air inlet (4), of the outer shell (1), an air outlet pipe (7) is connected to the air outlet (8), the head end of the air outlet pipe (7) extends into the air outlet (8), and the tail end of the air outlet pipe (7) penetrates through the outer shell (1), extends into the inner shell (2) and is communicated with the radiating pipe (9).

3. The high-rotation-speed aeroturbine engine according to claim 1, wherein the rotating shaft (3) is arranged in the inner shell (2), and the inner shell (2), the rotating shaft (3) and the radiating pipe (9) are axisymmetric.

4. The high-rotation-speed aeroturbine engine according to claim 1, wherein the wall of the radiating pipe (9) is of a hollow structure, a plurality of radiating fins (10) are distributed in the radiating pipe (9), and the radiating fins (10) are of a hollow structure and are communicated with the wall of the radiating pipe (9) at two ends.

5. The high-speed aeroturbine engine according to claim 4, wherein the plurality of cooling fins (10) are divided into a first plate group and a second plate group, the first plate group and the second plate group are symmetrically arranged in the cooling tube (9), a distance between two adjacent cooling fins (10) in the first plate group is a first interval (11), a distance between the first plate group and the second plate group is a second interval (12), the second interval (12) is larger than the first interval (11), and the second interval (12) is larger than a diameter of the rotating shaft (3).

6. A high speed aero turbine engine according to claim 4, wherein the cooling fin (10) is provided with a drainage groove at one end close to the turbine engine air inlet, said drainage groove being of conical configuration.