CN214273801U

CN214273801U - Turbocharging system applied to aviation heavy oil piston engine

Info

Publication number: CN214273801U
Application number: CN202120322522.9U
Authority: CN
Inventors: 李宁
Original assignee: Nanjing Norma Electronic Technology Co ltd
Current assignee: Nanjing Norma Electronic Technology Co ltd
Priority date: 2021-02-04
Filing date: 2021-02-04
Publication date: 2021-09-24
Anticipated expiration: 2031-02-04

Abstract

The utility model discloses a be applied to turbocharged system of aviation heavy oil piston engine, the cylinder inlet end of engine is connected with air intake manifold, air intake manifold passes through the tube coupling intercooler, the pipeline passes through the gas outlet of tee junction second grade booster. The utility model discloses on one-level turbocharging's basis, increase second grade turbocharging (electric turbocharging), utilize second grade electric turbocharging to compensate the not enough defect of one-level turbocharging high altitude air input, can satisfy the aircraft demand of flying in the high altitude more than 8000m, help promoting aviation heavy oil engine flying height.

Description

Turbocharging system applied to aviation heavy oil piston engine

Technical Field

The utility model relates to an aviation heavy oil piston engine field, concretely relates to aviation heavy oil piston engine second grade electric turbocharging technique.

Background

Along with the increase of the flying height of the aviation heavy oil piston engine, the output power of the engine can be attenuated, so that the flying height of the aircraft is influenced, and the requirement of high-altitude flying is difficult to meet. In order to improve the flying height of an aircraft and make up the problem of insufficient high-altitude air inflow of an engine, a one-stage turbocharging technology is generally adopted at the present stage, and the one-stage turbocharging mode mainly comprises exhaust gas turbocharging, mechanical turbocharging and the like. Research shows that the aviation heavy oil piston engine adopting the one-stage turbocharging can keep the maximum power to continuously work in the air with the height of 5000m, and the air inflow can not meet the air inflow requirement of the engine in the air with the height of more than 8000m, so that the power output of the engine is insufficient or the engine is flamed out.

The exhaust gas turbocharging utilizes the exhaust pressure of the engine to drive turbine blades, and the linked turbine blades further increase the air inflow of the engine; mechanical turbocharging utilizes an engine gear to drive turbine blades, which in turn increase the intake air flow of the engine, and the engine exhaust drive capability or gear drive capability determines the capacity of the turbocharger for intake air flow. Along with the increase of the flying height, the output power of the engine is reduced, the exhaust pressure is reduced/the gear rotating speed is reduced, the air inflow is reduced, the output power is reduced again until the output power of the engine is kept balanced and limited by the first-stage turbocharging (passive supercharging) capacity of the engine, and the conventional turbocharging system cannot meet the air supply requirement of high-altitude flight above 8000 m.

Disclosure of Invention

The utility model aims to solve the technical problem that realize a turbocharging system that can satisfy aircraft 8000m above high altitude flight demand.

In order to realize the purpose, the utility model discloses a technical scheme be: the utility model provides a be applied to turbocharged system of aviation heavy oil piston engine, the cylinder inlet end of engine is connected with air intake manifold, air intake manifold passes through the tube coupling intercooler, the gas outlet of pipeline through tee junction second grade booster.

The two-stage supercharger is an electric turbocharger, turbine blades of the electric turbocharger are driven by a motor, a power supply end of the motor is connected with an inverter, and the inverter is connected with the controller and receives pulse signals of the controller.

And a pressure sensor is arranged in the air inlet manifold, is connected with the controller and transmits a pressure signal in the air inlet manifold to the controller.

The system is equipped with the one-level booster, the one-level booster is exhaust gas turbocharger, the end connection of giving vent to anger of engine cylinder divides two the tunnel, wherein connects the power supply entry of one-level booster all the way, and another way is through bleed valve connection gas vent, the intercooler is connected to the gas outlet of one-level booster.

The air release valve is connected with the ECU and receives a control signal of the ECU.

The system is provided with a first-stage supercharger, the first-stage supercharger is a mechanical turbocharger, and an air outlet of the mechanical turbocharger is connected with an intercooler.

The utility model discloses on one-level turbocharging's basis, increase second grade turbocharging (electric turbocharging), utilize second grade electric turbocharging to compensate the not enough defect of one-level turbocharging high altitude air input, can satisfy the aircraft demand of flying in the high altitude more than 8000m, help promoting aviation heavy oil engine flying height.

Drawings

The following brief descriptions of the contents expressed by each figure and the marks in the figures in the specification of the present invention are as follows:

FIG. 1 is a schematic diagram of a turbocharging system for an aviation heavy oil piston engine;

FIG. 2 is a schematic diagram of the two-stage supercharger of FIG. 1;

the labels in the above figures are: 1. a cylinder; 2. a first stage supercharger; 3. a secondary supercharger; 4. an intercooler; 5. an intake manifold; 6. a pressure sensor; 7. a deflation valve; 8. a controller; 9. an inverter; 10. a turbine blade; 11. an electric motor.

Detailed Description

The following description of the embodiments with reference to the drawings is intended to illustrate the present invention in further detail, such as the shapes and structures of the components, the mutual positions and connections between the components, the functions and working principles of the components, the manufacturing process, and the operation and use methods, etc., so as to help those skilled in the art understand the present invention more completely, accurately and deeply.

In consideration of the difficulty of designing the electric turbocharger, the convenience of installation and maintenance and the like, as shown in fig. 1, the electric turbocharger, namely the primary supercharger 2, is installed between the intercooler 4 and the intake manifold 5, a three-way connection mode is adopted, the existing engine accessory system and the ECU control system are not changed, namely a three-way is arranged on a connecting pipeline between the intake manifold 5 and the intercooler 4, and an air outlet of the secondary supercharger 3 is connected through the three-way.

As shown in fig. 2, the turbine blades 10 of the electric turbocharger are driven by a motor 11, a power supply terminal of the motor 11 is connected to an inverter 9, and the inverter 9 is connected to the controller 8 and receives a pulse signal from the controller 8. A pressure sensor 6 is arranged in the intake manifold 5, and the pressure sensor 6 is connected with a controller 8 and transmits a pressure signal in the intake manifold 5 to the controller 8. In this way, the controller 8 controls the output pulse frequency according to the feedback manifold pressure, and further controls the rotating speed of the motor 11, the rotating speed of the turbine blade 10, and the air inflow of the air inlet and the air outlet, so as to maintain the air inflow required by the output power of the engine.

The system is provided with a first-stage supercharger 2, the first-stage supercharger 2 can adopt exhaust gas turbocharging, mechanical turbocharging and the like, and if the first-stage supercharger 2 is a mechanical turbocharger, an air outlet of the mechanical turbocharger is connected with an intercooler 4. If the first-stage supercharger 2 is an exhaust gas turbocharger, the air outlet end of the engine cylinder 1 is connected with two paths, wherein one path is connected with the power source inlet of the first-stage supercharger 2, the other path is connected with the air outlet through an air release valve 7, and the air outlet of the first-stage supercharger 2 is connected with an intercooler 4. Wherein the air release valve 7 is connected with the ECU and receives the control signal of the ECU.

The pressure of the intake manifold 5 is reduced along with the increase of the height of the aircraft, and the air intake amount is required to be increased in order to maintain the manifold intake pressure, and the opening degree of a first-stage turbocharger deflation valve 7 is required to be controlled by the ECU to increase the air intake amount; when the flying height of the aircraft reaches a certain height, the pressure ratio and the rotating speed of the first-stage turbocharger can reach the use limit, the first-stage turbocharger is difficult to continuously increase the air inflow, the electric turbocharger is started to increase the air inflow at the moment, the pressure of the manifold is maintained, and the output power of the engine is ensured.

The present invention has been described above with reference to the accompanying drawings, and it is to be understood that the invention is not limited to the specific embodiments described above, and that the invention is not limited to the specific embodiments described above, but rather is intended to cover various insubstantial modifications of the inventive method and solution, or its application to other applications without modification.

Claims

1. The utility model provides a be applied to turbocharged system of aviation heavy oil piston engine, the cylinder inlet end of engine is connected with air intake manifold, air intake manifold passes through the tube coupling intercooler, its characterized in that: the pipeline is connected with the air outlet of the secondary supercharger through a tee joint.

2. The turbocharging system applied to an aviation heavy oil piston engine, according to claim 1, wherein: the two-stage supercharger is an electric turbocharger, turbine blades of the electric turbocharger are driven by a motor, a power supply end of the motor is connected with an inverter, and the inverter is connected with the controller and receives pulse signals of the controller.

3. The turbocharging system applied to an aviation heavy oil piston engine, according to claim 2, wherein: and a pressure sensor is arranged in the air inlet manifold, is connected with the controller and transmits a pressure signal in the air inlet manifold to the controller.

4. The turbocharging system applied to an aviation heavy oil piston engine according to claim 1, 2 or 3, wherein: the system is equipped with the one-level booster, the one-level booster is exhaust gas turbocharger, the end connection of giving vent to anger of engine cylinder divides two the tunnel, wherein connects the power supply entry of one-level booster all the way, and another way is through bleed valve connection gas vent, the intercooler is connected to the gas outlet of one-level booster.

5. The turbocharging system applied to an aviation heavy oil piston engine, according to claim 4, wherein: the air release valve is connected with the ECU and receives a control signal of the ECU.

6. The turbocharging system applied to an aviation heavy oil piston engine according to claim 1, 2 or 3, wherein: the system is provided with a first-stage supercharger, the first-stage supercharger is a mechanical turbocharger, and an air outlet of the mechanical turbocharger is connected with an intercooler.