CN212359957U

CN212359957U - Primary and secondary type distributed aviation turbine power system driven by air-entraining combustion

Info

Publication number: CN212359957U
Application number: CN202021078319.3U
Authority: CN
Inventors: 宋志平; 王健; 姚远; 陈喆; 刘林涛; 李资晨
Original assignee: Xian Jiaotong University
Current assignee: Xian Jiaotong University
Priority date: 2020-06-11
Filing date: 2020-06-11
Publication date: 2021-01-15
Anticipated expiration: 2030-06-11

Abstract

The utility model discloses a bleed combustion driven primary and secondary type distributing type aviation turbine driving system, the utility model discloses a main engine has undertaken driving system's most weight, and the sub-engine light in weight that the distributing type was arranged, because do not have high-low pressure compressor, relevant casket, supporting mechanism in the sub-engine, greatly reduced the weight of sub-engine totality. Meanwhile, under the same output power, the gas flow of the sub-engine is about 25 percent of that of the conventional engine, and the weight of the combustion chamber is greatly reduced; under the same power condition, the weight of the sub engine is greatly reduced. Under the same performance parameters, the lift-drag ratio of the aircraft is improved by reducing the weight of the sub-engines, so that the overall performance of the aircraft is optimal.

Description

Primary and secondary type distributed aviation turbine power system driven by air-entraining combustion

Technical Field

The utility model belongs to the aviation field, concretely relates to bleed combustion driven primary and secondary type distributing type aviation turbine driving system.

Background

Distributed power systems have been a hotspot in research in the field of aviation in recent years. The distributed power system can improve the propelling efficiency of the power system, wherein a distributed electric propeller or an electric fan can be matched, the equivalent bypass ratio of an engine is increased, the propelling efficiency is improved, and the oil consumption rate is reduced; meanwhile, the boundary layer resistance of the airplane is reduced, the lift-drag ratio of the airplane is improved, and the integrated benefit of the flying is improved through the free layout of the distributed electrically-driven fan/propeller.

A 'primary-secondary type' distributed aviation turbine power system based on bleed air combustion driving is novel efficient distributed power. At present, the scheme is blank in the domestic model field, and no relevant model research or pre-research report exists internationally.

Both the integrated design of the flying and the integrated design and the distributed power are the research hotspots at home and abroad for a long time. Especially, the electric drive distributed power facing to the tilt rotor and the distributed electric propulsion of the wing back engine belong to the category of a primary-secondary type power system, and a great deal of consideration is made on the aspect of flight and hair integration. The idea of the distributed turbine engine of the project is to greatly reduce the weight of the distributed engine, and is a supplement to the electric drive distributed power with higher efficiency.

The integrated design of the flying engine is to find the optimal overall layout, use control mode and energy utilization mode of the flying engine under the tactical technical index requirements and constraint conditions of the airplane so as to obtain high-efficiency inside and outside aerodynamic characteristics and good flight performance and flight quality in the whole flight envelope and meet the requirements of airplane thrust and energy in different flight stages. The integrated design of the flying and the flying faces the problems of the tight coupling of the internal flow and the external flow of the airplane, the comprehensive weight reduction design of the structure, the high-precision self-adaptive control, the heat management, the performance integration and the like. The distributed power is equivalent to dividing the engine into a plurality of small engines, and is beneficial to the integrated design layout of the airplane.

Disclosure of Invention

An object of the utility model is to overcome the aforesaid not enough, provide a primary and secondary type distributing type aviation turbine driving system of bleed combustion drive, can be under same performance parameter, through reducing sub-engine weight, improve the lift-drag ratio of aircraft to realize that aircraft overall performance is optimal.

In order to achieve the purpose, the utility model discloses a mother engine and a son engine, the mother engine is connected with the son engine through a pipeline;

the female engine comprises an air inlet pipeline, the air inlet pipeline is connected with a female engine compressor, the female engine compressor is connected with a female engine diffuser, the female engine diffuser is connected with a female engine combustion chamber and a female engine diffuser shell, and the female engine diffuser shell is connected with a pipeline;

the sub-engine comprises a sub-engine combustion chamber, and the sub-engine combustion chamber is connected with a pipeline.

The combustion chamber of the primary engine is connected with a turbine stator of the primary engine, a turbine rotor of the primary engine is arranged in the turbine stator of the primary engine, the turbine rotor of the primary engine is fixed on a shaft of the primary engine, the shaft of the primary engine is arranged on a bearing shaft of the primary engine, and a tail nozzle of the primary engine is arranged behind the turbine rotor of the primary engine.

The sub-engine combustion chamber is connected with a sub-engine turbine stator, a sub-engine turbine rotor is arranged in the sub-engine turbine stator, the sub-engine turbine rotor is fixed on a sub-engine shaft, the sub-engine shaft is arranged on a sub-engine bearing shaft, and a sub-engine tail nozzle is arranged behind the sub-engine turbine rotor.

The duct is part of the wing support structure.

The sub-engines are arranged on two sides of the main engine and are symmetrical with the center of the main engine.

Compared with the prior art, the utility model discloses a main engine has undertaken most weight of driving system, and the sub-engine light in weight that the distributing type was arranged, because do not have high-low pressure compressor, relevant casket, supporting mechanism in the sub-engine, greatly reduced the total weight of sub-engine. Meanwhile, under the same output power, the gas flow of the sub-engine is about 25 percent of that of the conventional engine, and the weight of the combustion chamber is greatly reduced; under the same power condition, the weight of the sub engine is greatly reduced. Under the same performance parameters, the lift-drag ratio of the aircraft is improved by reducing the weight of the sub-engines, so that the overall performance of the aircraft is optimal.

Drawings

Fig. 1 is a front view of the present invention;

fig. 2 is a top view of the present invention;

FIG. 3 is a cross-sectional view of a midengine of the present invention;

fig. 4 is a cross-sectional view of a neutron engine of the present invention;

1-pipeline, 2-mother engine, 3-child engine, 4-mother engine diffuser shell, 5-mother engine shaft, 6-mother engine compressor, 7-mother engine bearing shaft, 8-mother engine diffuser, 9-mother engine combustion chamber, 10-mother engine turbine stator, 11-mother engine turbine rotor, 12-mother engine tail nozzle, 13-child engine shaft, 14-child engine bearing shaft, 15-child engine combustion chamber, 16-child engine turbine stator, 17-child engine turbine rotor and 18-child engine tail nozzle.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

Referring to fig. 1 and 2, the utility model comprises a mother engine 2 and a son engine 3, wherein the mother engine 2 is connected with the son engine 3 through a pipeline 1; the pipeline 1 is part of a wing support structure. The sub-engines 3 are disposed on both sides of the parent engine 2 and are symmetrical about the center of the parent engine 2.

Referring to fig. 3, the parent engine 2 comprises an air inlet pipeline, the air inlet pipeline is connected with a parent engine compressor 6, the parent engine compressor 6 is connected with a parent engine diffuser 8, the parent engine diffuser 8 is connected with a parent engine combustion chamber 9 and a parent engine diffuser shell 4, and the parent engine diffuser shell 4 is connected with a pipeline 1; the primary engine combustion chamber 9 is connected with a primary engine turbine stator 10, a primary engine turbine rotor 11 is arranged in the primary engine turbine stator 10, the primary engine turbine rotor 11 is fixed on a primary engine shaft 5, the primary engine shaft 5 is arranged on a primary engine bearing shaft 7, and a primary engine tail nozzle 12 is arranged behind the primary engine turbine rotor 11.

Referring to fig. 4, the sub-engine 3 includes a sub-engine combustion chamber 15, and the sub-engine combustion chamber 15 is connected to the pipe 1. The sub-engine combustion chamber 15 is connected with a sub-engine turbine stator 16, a sub-engine turbine rotor 17 is arranged in the sub-engine turbine stator 16, the sub-engine turbine rotor 17 is fixed on a sub-engine shaft 13, the sub-engine shaft 13 is arranged on a sub-engine bearing shaft 14, and a sub-engine tail nozzle 18 is arranged behind the sub-engine turbine rotor 17.

The utility model discloses a primary and secondary type driving system through power distribution and the weight distribution between the matching power, realizes the pneumatic integrated overall arrangement that flies of efficient, improves the lift-drag ratio of aircraft. For the tilt rotor aircraft, the wing span of the aircraft is increased, and therefore the horizontal flight lift drag ratio is increased. For the flying wing layout aircraft with the back-mounted power, the flow field matching drag reduction is facilitated, and the lift-drag ratio of the aircraft is improved.

The utility model discloses a power distribution and distributed drive screw or fan of son, mother's power realize appropriate big duct ratio, can improve driving system's propulsive efficiency.

Bleed combustion drive turbine does work is the utility model discloses a showing characteristics, the bleed pipeline must with aircraft structure integrated design, just can compensate the weight gain that the bleed pipeline brought.

The thrust-weight ratio/power-weight ratio of the sub-engine system exceeds 30 by the overall matching design of the primary-secondary type distributed aviation turbine power system driven by bleed air combustion, and the oil consumption rate of the engine is reduced by 5% by the distributed matching bypass ratio design.

The utility model discloses a main engine has born the most weight of driving system, and the sub-engine light in weight that the distributing type was arranged, nevertheless thrust/power is big, and thrust/power-to-weight ratio can reach more than 30. Because the bleed air pressure is high, the density is large, and the flow velocity of the bleed air is relatively slow (smaller than the mach number of bypass air of a conventional turbofan engine), the total pressure loss of the bleed air transmission is controllable. Because the sub-engine is not provided with a high-low pressure compressor, a related casing and a supporting mechanism, the weight can be reduced by about 35-40%; the high-low pressure turbine (guider and rotor) and the matched casing of the engine are eliminated, and the weight is reduced by about 14 to 18 percent. Meanwhile, under the same output power, the gas flow of the sub-engine is about 25 percent of that of the conventional engine, and the weight of the combustion chamber is greatly reduced; although the number of stages of the power turbine (typically 2-3 stages, associated with the design of the overall engine pressure ratio) is increased over the original power turbine, the weight gain of the power turbine is limited due to the reduced gas flow. Therefore, conservative calculations, sub-engine weight loss can exceed 70% or more at the same power/thrust.

Claims

1. A primary-secondary type distributed aviation turbine power system driven by bleed air combustion is characterized in that a primary engine (2) and a secondary engine (3) are connected through a pipeline (1), wherein the primary engine (2) is connected with the secondary engine (3);

the primary engine (2) comprises an air inlet pipeline, the air inlet pipeline is connected with a primary engine air compressor (6), the primary engine air compressor (6) is connected with a primary engine diffuser (8), the primary engine diffuser (8) is connected with a primary engine combustion chamber (9) and a primary engine diffuser shell (4), and the primary engine diffuser shell (4) is connected with a pipeline (1);

the sub-engine (3) comprises a sub-engine combustion chamber (15), and the sub-engine combustion chamber (15) is connected with the pipeline (1).

2. The bleed air combustion driven primary-secondary distributed aircraft turbine power system according to claim 1, characterized in that the primary engine combustion chamber (9) is connected to a primary engine turbine stator (10), a primary engine turbine rotor (11) is arranged in the primary engine turbine stator (10), the primary engine turbine rotor (11) is fixed on the primary engine shaft (5), the primary engine shaft (5) is arranged on the primary engine bearing shaft (7), and a primary engine tail nozzle (12) is arranged behind the primary engine turbine rotor (11).

3. A bleed air combustion driven, child-mother distributed aircraft turbine power system according to claim 1, characterised in that the child engine combustion chamber (15) is connected to a child engine turbine stator (16), in which child engine turbine rotor (17) is arranged in the child engine turbine stator (16), the child engine turbine rotor (17) being fixed to the child engine shaft (13), the child engine shaft (13) being arranged on a child engine bearing shaft (14), behind the child engine turbine rotor (17) there being arranged a child engine exhaust nozzle (18).

4. A bleed air combustion driven, child-mother distributed aircraft turbine power system according to claim 1, characterised in that the pipeline (1) is part of a wing support structure.

5. A bleed air combustion driven, parent and child distributed aircraft turbine power system according to claim 1, characterised in that the child engines (3) are arranged on both sides of the parent engine (2) and are centrosymmetric to the parent engine (2).