阅读说明：本技术 一种具有轴承降温功能的两涵道涡轮喷气式发动机 (Two-duct turbine jet engine with bearing cooling function ) 是由 赵景山 张家悦 于 2020-06-08 设计创作，主要内容包括：本发明公开了一种具有轴承降温功能的两涵道涡轮喷气式发动机,包括涵道、设置在所述涵道的进气端的进气机构和设置在所述涵道的出气端的尾喷管,所述涵道包括外涵道和位于所述外涵道内的内涵道,所述外涵道和所述内涵道分别与所述尾喷管连通,所述外涵道和所述内涵道分别与所述进气机构连通。与传统涡轮喷气式发动机相比,本发明提供的具有轴承降温功能的两涵道涡轮喷气式发动机降低了发动机工作时轴承工作区域的温度,减少了发动机成本,延长了发动机寿命,改善了发动机性能。(The invention discloses a two-duct turbojet engine with a bearing cooling function, which comprises a duct, an air inlet mechanism arranged at the air inlet end of the duct and a tail spray pipe arranged at the air outlet end of the duct, wherein the duct comprises an outer duct and an inner duct positioned in the outer duct, the outer duct and the inner duct are respectively communicated with the tail spray pipe, and the outer duct and the inner duct are respectively communicated with the air inlet mechanism. Compared with the traditional turbojet engine, the two-duct turbojet engine with the bearing cooling function provided by the invention has the advantages that the temperature of a bearing working area is reduced when the engine works, the engine cost is reduced, the service life of the engine is prolonged, and the engine performance is improved.)

1. The utility model provides a two duct turbojet engines with bearing cooling function which characterized in that: the bypass comprises an outer bypass and an inner bypass positioned in the outer bypass, the outer bypass and the inner bypass are respectively communicated with the tail spray pipe, and the outer bypass and the inner bypass are respectively communicated with the air inlet mechanism.

2. The two-duct turbojet engine with bearing cooling of claim 1, wherein: the inner duct comprises an inner duct shell, a main shaft rotationally connected with the inner duct shell through a bearing, and an impeller and a turbine which are fixedly connected to the main shaft, wherein the impeller is close to the air inlet mechanism, and the turbine is close to the tail nozzle.

3. The two-duct turbojet engine with bearing cooling of claim 2, wherein: the air inlet mechanism comprises an air inlet channel and a diffuser fixedly connected in the air inlet channel, and the diffuser and the impeller form a gas turbine.

4. The two-duct turbojet engine with bearing cooling of claim 3, wherein: and a guide plate is arranged at one end of the inner bypass casing close to the turbine, and the guide plate is fixedly connected with the inner bypass casing.

5. The two-duct turbojet engine with bearing cooling of claim 4, wherein: the outer duct comprises an outer duct shell, the air inlet mechanism and the inner duct are both located in the outer duct shell, a turbine stator is further arranged in the outer duct shell, and the turbine stator and the turbine rotor are combined into a turbine.

6. The two-duct turbojet engine with bearing cooling of claim 5, wherein: and a combustion chamber is also arranged in the outer bypass casing and is positioned between the gas turbine and the turbine.

7. The two-duct turbojet engine with bearing cooling of claim 1, wherein: the diameter of the tail nozzle is gradually reduced along the direction from the air inlet end to the air outlet end.

Technical Field

The invention relates to the technical field of engines, in particular to a two-duct turbojet engine with a bearing cooling function.

Background

In 1903, the laite brother was successfully tried to fly the controlled fixed wing aircraft for the first time. In the following century, aviation airplanes have brought about a skyward change in human society. A great deal of scientific research and development is put into all countries in the world to develop the aviation aircraft technology, and the most key technology in the aviation aircraft technology is the aircraft engine technology.

Before the 40's of the 20 th century, most aircraft employed piston engines. The engine can only output torque but can not directly generate pulling force or pushing force, so the engine is often matched with a propeller. The propeller rotates under the driving of the engine to generate pulling force on the blades. As the aircraft flight speed increases, the linear velocity of the airflow at the blade tip increases greatly, causing the engine efficiency to decrease greatly, thus greatly limiting the flight speed. After the 40's of the 20 th century, several western countries began developing and using turbojet engines. The turbojet engine consists of five parts, namely an air inlet device, an air compressor, a combustion chamber, a turbine and a tail nozzle. Compared with a piston engine, the processes of air intake, combustion, expansion, work application, exhaust and the like of the turbojet engine are completed by different parts at the same time, so that the working efficiency is improved. Meanwhile, under the action of a gas turbine at the front end of the turbojet engine, the air input of the turbojet engine is far higher than that of the piston engine, so that the running power of the turbojet engine is greatly improved compared with that of the piston engine. However, during engine operation, the turbine temperature after the combustor is extremely high, approximately 500 ℃ to 700 ℃. The extremely high operating temperature is undoubtedly a great challenge for critical components such as bearings. On the one hand, the existing lubricants are difficult to lubricate effectively at such high temperatures, and on the other hand, the rotating parts have a very short working life at high temperatures. In recent years, scientists and engineers have invested a great deal of time, effort and money in developing bearings that can operate efficiently at high temperatures. If the temperature of the bearing working area can be reduced to a reasonable range, the cost of the engine is greatly reduced, the service life of the engine is prolonged, and the performance of the engine is improved.

Therefore, it is an urgent technical problem to be solved in the art to provide a two-duct turbojet engine with a bearing cooling function to reduce the engine cost, prolong the engine life and improve the engine performance.

Disclosure of Invention

The invention aims to provide a two-duct turbojet engine with a bearing cooling function, which is used for solving the problems in the prior art, reducing the temperature of a bearing working area when the engine works, reducing the cost of the engine, prolonging the service life of the engine and improving the performance of the engine.

In order to achieve the purpose, the invention provides the following scheme:

the invention provides a two-duct turbojet engine with a bearing cooling function, which comprises a duct, an air inlet mechanism arranged at the air inlet end of the duct and a tail nozzle arranged at the air outlet end of the duct, wherein the duct comprises an outer duct and an inner duct positioned in the outer duct, the outer duct and the inner duct are respectively communicated with the tail nozzle, and the outer duct and the inner duct are respectively communicated with the air inlet mechanism.

Preferably, the inner duct comprises an inner duct shell, a main shaft rotationally connected with the inner duct shell through a bearing, and an impeller and a turbine which are fixedly connected to the main shaft, wherein the impeller is close to the air inlet mechanism, and the turbine is close to the tail nozzle.

Preferably, the air inlet mechanism comprises an air inlet and a diffuser fixedly connected in the air inlet, and the diffuser and the impeller form a gas turbine.

Preferably, a guide plate is arranged at one end, close to the turbine, of the inner duct shell, and the guide plate is fixedly connected with the inner duct shell.

Preferably, the outer duct comprises an outer duct shell, the air inlet mechanism and the inner duct are both located in the outer duct shell, a turbine stator is further arranged in the outer duct shell, and the turbine stator and the turbine are combined to form the turbine.

Preferably, a combustion chamber is further disposed in the outer bypass casing, and the combustion chamber is located between the gas turbine and the turbine.

Preferably, the diameter of the tail pipe is gradually reduced along the direction from the air inlet end to the air outlet end.

Compared with the prior art, the invention has the following technical effects:

the two-duct turbojet engine with the bearing cooling function reduces the temperature of a bearing working area when the engine works, reduces the cost of the engine, prolongs the service life of the engine and improves the performance of the engine. In the working process, air is divided into two parts after passing through the air inlet mechanism and respectively enters the inner duct and the outer duct; the air entering the inner duct flows along the inner duct, cools key rotating parts such as a main shaft, a bearing and the like, and is discharged from a tail nozzle through a turbine; the air entering the outer duct flows into the combustion chamber, is fully mixed with fuel and then is combusted, pushes the turbine and is discharged from the tail nozzle at high speed. The two-bypass turbojet engine with the bearing cooling function can control the temperature of the bearing near the turbine to be 300-400 ℃, and meets the working temperature range of a common bearing. The inner culvert continuously flows low-temperature air into the inner culvert to cool key rotating parts such as the bearing, the working temperature of the key rotating parts such as the bearing is reduced, the failure of lubricating liquid at high temperature is avoided, the service life of the key rotating parts such as the bearing is prolonged, the performance of the engine is improved, and the service life of the engine is prolonged. The aero-engine is a core component of an aero-plane, the improvement of the working performance of the aero-engine is beneficial to the improvement of the flight performance of the aero-plane, and the aero-engine has important economic, environmental and social significance.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a first schematic structural view of a two-duct turbojet engine with a bearing cooling function according to the present invention;

FIG. 2 is a schematic structural diagram II of a two-duct turbojet engine with a bearing cooling function according to the present invention;

wherein: 1-an air intake mechanism; 2-an inner duct; 3-an external duct; 4-a turbine; 5-tail nozzle; 6-a turbine; 7-a flow guide plate; 8-a bearing; 9-a main shaft; 10-a combustion chamber; 11-a diffuser; 12-an impeller; 13-air intake duct.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.

The invention aims to provide a two-duct turbojet engine with a bearing cooling function, so as to reduce the temperature of a bearing working area when the engine works, reduce the cost of the engine, prolong the service life of the engine and improve the performance of the engine.

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.

As shown in fig. 1 to 2: the two-duct turbojet engine with the bearing cooling function comprises a duct, an air inlet mechanism 1 arranged at the air inlet end of the duct and a tail nozzle 5 arranged at the air outlet end of the duct.

Wherein, the duct includes outer duct 3 and is located the interior duct 2 of outer duct 3, and outer duct 3 and interior duct 2 communicate with exhaust nozzle 5 respectively, and outer duct 3 and interior duct 2 communicate with mechanism 1 that admits air respectively. The inner duct 2 comprises an inner duct shell, a main shaft 9 and a turbine 6, wherein the main shaft 9 is rotatably connected with the inner duct shell through a bearing 8, the turbine 6 is fixedly connected onto the main shaft 9, the turbine 6 is close to the tail nozzle 5, the diameter of the tail nozzle 5 is gradually reduced along the direction from the air inlet end to the air outlet end, and the inner duct has good aerodynamic characteristics.

The air inlet mechanism 1 comprises an air inlet 13 and a diffuser 11 fixedly connected in the air inlet 13, and an impeller 12 is fixedly connected with a main shaft 9 in the inner duct 2. The impeller 12 and diffuser 11 constitute a compressor turbine. A guide plate 7 is arranged at one end of the inner bypass casing close to the turbine 4, and the guide plate 7 is fixedly connected with the inner bypass casing.

The outer duct 3 comprises an outer duct shell, the air inlet mechanism 1 and the inner duct 2 are both located in the outer duct shell, a turbine stator is further arranged in the outer duct shell, and the turbine stator and the turbine 6 are combined into a turbine 4. Also disposed within the outer ducted housing is a combustor 10, the combustor 10 being located between the compressor turbine and the turbine 4.

The working process of the two-duct turbojet engine with the bearing cooling function is as follows:

the air is divided into two parts after passing through the air inlet mechanism 1, and the two parts respectively enter an inner duct 2 and an outer duct 3; the air entering the inner duct 2 flows along the inner duct 2, cools key rotating parts such as the main shaft 9 and the bearing 8 and the like, and is discharged from the tail nozzle 5 through the turbine 6, so that the working temperature of the key rotating parts such as the bearing 8 and the like is reduced, the failure of lubricating liquid at high temperature is avoided, the service life of the key rotating parts such as the bearing 8 and the like is prolonged, the performance of the engine is further improved, and the service life of the engine is prolonged; the air entering the outer duct 3 enters the combustion chamber 10, is fully mixed with fuel and then is combusted, the turbine 6 is pushed and is discharged from the tail nozzle 5 at a high speed, and the rotation of the turbine 6 drives the rotation of the gas turbine 11, so that the gas turbine operates circularly.

The principle and the implementation mode of the present invention are explained by applying specific examples in the present specification, and the above descriptions of the examples are only used to help understanding the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.