CN217129636U

CN217129636U - Anti-surge and energy recovery control device for turbocharger of aviation piston engine

Info

Publication number: CN217129636U
Application number: CN202221473761.5U
Authority: CN
Inventors: 刘晓静; 杜发荣
Original assignee: Beijing Lingdong Guochuang Technology Co ltd
Current assignee: Beijing Lingdong Guochuang Technology Co ltd
Priority date: 2022-06-13
Filing date: 2022-06-13
Publication date: 2022-08-05
Anticipated expiration: 2032-06-13

Abstract

The utility model discloses an anti-surge and energy recuperation controlling means for aviation piston engine turbocharger, including flow control and energy recuperation subassembly, negative pressure control solenoid valve, vacuum pump, controller, servo motor, three way connection, pressure sensor, super capacitor, power vary voltage module, servo motor is low pressure direct current type motor, link firmly with the choke valve of flow control and energy recuperation subassembly, the air inlet of flow control and energy recuperation subassembly passes through the pipe connection with the gas outlet of compressor, the top interface of energy recuperation subassembly passes through the negative pressure union coupling with three way connection, three way connection passes through the negative pressure union coupling with negative pressure control solenoid valve, pressure sensor is connected with three way connection, negative pressure control solenoid valve passes through the pipeline and is connected with the vacuum pump, negative pressure control solenoid valve passing signal line is connected with the controller. The utility model discloses can realize the recycle of unnecessary waste gas energy in the compressor when preventing the compressor surge.

Description

Anti-surge and energy recovery control device for turbocharger of aviation piston engine

Technical Field

The invention relates to an aviation piston engine turbocharging technology, in particular to an anti-surge and energy recovery technology of an aviation piston engine turbocharger.

Background

Aviation piston engines are an important choice for general aircraft power. With the opening of the Chinese airspace, the adoption of the turbocharging technology is an effective way for solving the problems of high-altitude flight power reduction and high oil consumption, and the supercharger technology of the piston type aircraft engine determines the flight performance of the aircraft.

The exhaust gas turbocharger is widely applied to supercharging of aviation piston engines, and the working principle of the exhaust gas turbocharger is as follows: the exhaust gas exhausted by the engine is used as power to push the turbine of the supercharger and drive the coaxial compressor impeller to rotate at high speed. The compressed air is charged into the cylinder to increase the air inlet pressure and perform the function of pressurization. The air intake quantity is increased, the oil supply quantity is also increased, more combustible mixture is formed, and the power of the engine is increased by 20 to 30 percent.

The compressor is an important component of a waste turbocharger, when the rotating speed of the compressor is constant and the air inlet flow is reduced, the speed of gas in a flow channel is uneven and backflow phenomenon occurs, the compressor enters an unstable working state, and further, the air flow is suddenly large and small, the pressure value fluctuates severely, along with the severe vibration of the compressor, roaring sound or wheezing sound is generated, and the phenomenon is called surging of the compressor. In actual operation, surging should be avoided, but the efficient operating point of the compressor is often near the surging point, and surging of the compressor is difficult to avoid in order to obtain higher efficiency.

The effective method for solving the surge of the compressor is to add the anti-surge device, and the anti-surge device can discharge a part of air flow flowing out of the compressor when the flow required by the engine is too small, so that the surge of the compressor is avoided, and the flow requirement of the engine is also met.

The surge prevention device is mounted on an aircraft, and with the increasing electrification degree of the aircraft, the demand of the surge prevention device for electric energy is larger, and a larger battery needs to be mounted, which undoubtedly increases the self weight of the aircraft. And current anti-surge device often directly discharges into atmosphere or reintroduce back the compressor import with unnecessary waste gas in the compressor at present, and waste gas energy loss is more. The surge suppression control device of application No. 202120266888.9 and the surge control device of application No. 201510925322.1, though having a simple structure, have a low energy utilization rate of exhaust gas.

If a corresponding structure and a corresponding control system can be designed, when the surge of an engine is reduced, redundant waste gas energy in the compressor is converted into electric energy to be stored for supplying power to an electric appliance, so that the full utilization of energy can be realized, and the power-to-weight ratio of the aircraft is improved.

SUMMERY OF THE UTILITY MODEL

To the problem, the utility model provides an anti-surge and energy recuperation controlling means for aviation piston engine turbo charger is one kind and can prevent the booster surge to can turn into the electric energy with unnecessary discarded energy.

The utility model is used for aviation piston engine turbo charger's anti-surge and energy recuperation controlling means, adjust solenoid valve, vacuum pump, controller, servo motor, three way connection, first pressure sensor, second pressure sensor, super capacitor and power vary voltage module including flow control and energy recuperation subassembly, negative pressure.

The flow regulation and energy recovery assembly comprises a plunger, a valve cover, a shell, a conical power generation coil, a conical permanent magnet, a first return spring, a second return spring, a sliding rail and a choke valve.

The shell is provided with a cylindrical transverse shell and a cylindrical L-shaped structural shell of a longitudinal shell; meanwhile, an air outlet channel is designed on the side wall of the transverse shell; a choke valve is arranged at the air outlet of the air outlet channel through a rotating shaft; the plunger piston and the valve cover are coaxially sleeved inside and outside and are coaxially arranged in the longitudinal shell; the top end of the valve cover is provided with an interface communicated with the interior of the valve cover; the plunger is sleeved with a first return spring, and two ends of the first return spring are respectively fixed with the plunger and the valve cover;

the conical power generation coil is coaxially arranged in the transverse shell, and the small end face of the conical power generation coil is fixed with the outer end face of the transverse shell; a conical permanent magnet is coaxially sleeved outside the conical power generation coil; the conical permanent magnet has a moving amplitude along the self axial direction; second return springs which are arranged along the circumference are arranged between the small end of the conical permanent magnet and the end surface of the outer end of the transverse shell; one end of the second reset spring is fixed with the end face of the outer end of the transverse shell, and the other end of the second reset spring is fixedly connected with the end face of the small end of the conical permanent magnet;

in the flow regulation and energy recovery assembly, a rotating shaft of the choke valve is connected with an output shaft of the servo motor through a belt transmission mechanism; the air inlet at the bottom end of the longitudinal shell is connected with the air outlet of the air compressor through a pipeline; the connector at the top end of the valve cover is connected with the connecting end A of the three-way joint through a negative pressure pipe; the connecting end B of the three-way joint is connected with a negative pressure regulating electromagnetic valve through a negative pressure pipe; the negative pressure regulating electromagnetic valve is connected with the vacuum pump through a negative pressure pipeline; the negative pressure regulating electromagnetic valve is connected with the controller through a signal line; the connecting end C of the three-way joint is connected with a first pressure sensor, and the first pressure sensor measures the air pressure of the negative pressure pipe; the second pressure sensor is fixedly arranged in the transverse shell and is close to the air inlet of the air outlet channel; the signal lines of the first pressure sensor and the second pressure sensor are connected with a controller; the lead of the conical power generation coil is connected with the input end of the super capacitor; the output end of the super capacitor is connected with the input end of the power supply transformation module; the output end of the power supply voltage transformation module is connected with the servo motor, the controller, the negative pressure regulating electromagnetic valve and the vacuum pump.

When the gas flow in the gas compressor is overlarge, the controller drives the negative pressure regulating electromagnetic valve to work through a PWM signal to control the conduction time of the negative pressure pipe and the vacuum pump, meanwhile, the first pressure sensor feeds a pressure signal in the negative pressure pipe back to the controller to form a closed loop, then, under the action of pressure difference, the plunger overcomes the action of the first reset spring to move upwards, redundant gas flow enters the shell through a gap between the plunger and the bottom surface of the longitudinal shell, the conical permanent magnet is pushed to overcome the elastic force of the second reset spring group to move, and the cutting coil generates electricity; the generated electricity is stored by a super capacitor and supplies power for a servo motor, a controller, a negative pressure regulating electromagnetic valve and a vacuum pump;

under the condition that the choke valve is closed completely, if the air pressure in the shell is too high, the air in the air compressor can be blocked, therefore, the second pressure sensor is adopted to monitor the air pressure at the air inlet of the air outlet channel in real time and feed back the air pressure to the main controller, the main controller drives the servo motor to rotate, the servo motor adjusts the opening degree of the choke valve, and the unnecessary air flow in the air compressor is ensured to be discharged in time.

Compared with the prior art, the invention has the beneficial effects that:

the utility model discloses surge-proof and energy recovery controlling means can prevent the booster surge to can be with the device of unnecessary gas energy conversion electrical energy in the booster, make full use of waste energy is favorable to promoting the electrification of spacecraft, improve its power-to-weight ratio;

drawings

Fig. 1 is a schematic structural view of the anti-surge and energy recovery control device of the present invention.

Fig. 2 is a half-sectional view of the flow regulating and energy recovering assembly in the anti-surge and energy recovering control device of the present invention.

Fig. 3 is an axonometric view of the flow regulation and energy recovery assembly in the surge prevention and energy recovery control device of the present invention.

FIG. 4 is a schematic view of the location of the feedthrough holes in the flow conditioning and energy recovery assembly.

In the figure:

1-flow regulation and energy recovery assembly 2-negative pressure regulation electromagnetic valve 3-vacuum pump

4-controller 5-servo motor 6-three-way joint

7-first pressure sensor 8-second pressure sensor 9-supercapacitor

10-power transformation module 11-compressor 101-plunger

102-valve cover 103-shell 104-conical generating coil

105-conical permanent magnet 106-first return spring 107-second return spring

108-slide rail 109-choke valve 110-air outlet channel

111-lead hole

Detailed Description

The present invention will be further explained with reference to the accompanying drawings and examples, which are only used for explaining the present invention and do not limit the scope of the present invention.

The utility model is used for aviation piston engine turbo charger's anti-surge and energy recuperation controlling means, including flow control and energy recuperation subassembly 1, negative pressure adjusting solenoid valve 2, vacuum pump 3, controller 4, servo motor 5, three way connection 6, first pressure sensor 7, second pressure sensor 8, super capacitor 9 and power vary voltage module 10, as shown in fig. 1 ~ 3.

The flow regulating and energy recovering assembly 1 comprises a plunger 101, a valve cover 102, a shell 103, a conical power generation coil 104, a conical permanent magnet 105, a first return spring 106, a second return spring 107, a slide rail 108 and a choke valve 109.

Wherein the housing 103 has a cylindrical lateral housing and a cylindrical longitudinal housing; the inner end of the transverse shell is connected and communicated with the side wall of the upper part of the longitudinal shell to form an L-shaped structural shell; meanwhile, the side wall of the transverse shell is also provided with an arc-shaped air outlet channel 110, and an air outlet of the air outlet channel 110 faces the outer end of the transverse shell; and a choke valve 109 is installed at an air outlet of the air outlet passage 110. The two ends of the choke valve 109 are provided with rotating shafts which are respectively connected with the side walls of the air outlet channel 110 to form a rotating pair, and the choke valve 109 is driven to rotate by rotating the rotating shafts, so that the opening of the choke valve 109 can be adjusted, and further the air outlet quantity can be adjusted. The inner wall of the outer shell 103 (including the air outlet channel 110) is also provided with a honeycomb-shaped groove to reduce the working noise.

The plunger 101 and the valve cover 102 are both of cylindrical structures and are coaxially sleeved inside and outside; and both are coaxially arranged in the longitudinal shell. A shoulder is arranged on the top end of the valve cover 102 in the circumferential direction and is used for being matched with the top end face of the longitudinal shell to limit the downward movement of the valve cover 102; the top end of the valve cap 102 is designed with an interface communicated with the interior of the valve cap 102 for pipeline connection. Meanwhile, a shoulder designed on the circumferential direction of the bottom end of the plunger 101 is matched with an annular boss designed on the inner wall of the bottom of the longitudinal shell to limit the downward movement of the plunger 101. The plunger 101 is sleeved with a first return spring 106, and two ends of the first return spring 106 are respectively matched and fixed with a shoulder at the bottom of the plunger 101 and a shoulder designed on the outer wall at the bottom of the valve cover 102; meanwhile, the valve cover 102 is matched with the top surface of the longitudinal shell through a shoulder designed on the outer wall of the bottom of the valve cover 102, and the upward movement of the valve cover 102 is limited. The valve cap 102 is returned to the original position after moving upward by the elastic force of the first return spring 106.

The conical generating coil 104 is coaxially arranged in the transverse shell, the small end face of the conical generating coil 104 is fixed with the outer end face of the transverse shell, and a lead of the conical generating coil 104 is embedded into an iron core of the conical generating coil 104 and is led out from the small end of the conical generating coil 104 through a lead hole 111 on the outer end face of the transverse shell, as shown in fig. 4. The conical permanent magnet 103 is coaxially sleeved outside the conical generating coil 104, and a gap exists between the conical generating coil and the conical permanent magnet. A sliding block is designed on the side wall at the small end of the conical permanent magnet 105 and is installed in a matching way with the sliding rail 108; the slide rail 108 is axially arranged along the transverse part and fixedly mounted on the inner wall of the transverse shell, so that the conical permanent magnet 104 can axially slide along the transverse shell to cut the magnetic induction line to generate electricity. Second return springs 107 which are arranged along the circumference are arranged between the small end of the conical permanent magnet 104 and the end surface of the outer end of the transverse shell 103; one end of a second reset spring 107 is fixed with the end face of the outer end of the transverse shell, and the other end of the second reset spring is fixedly connected with the end face of the small end of the conical permanent magnet 104; the return of the tapered permanent magnet 105 after sliding is achieved by the second return spring 107.

In the flow rate control and energy recovery module 1, the opening degree of the choke valve 109 is controlled by a servo motor. The servo motor 5 is a low voltage dc type motor, and the output end is connected to the choke valve 109 in the flow rate adjusting and energy recovering assembly 1 through a belt transmission mechanism. The belt transmission mechanism comprises two belt pulleys and a transmission belt. The two belt pulleys are respectively and fixedly arranged on a rotating shaft of the choke valve 109 and an output shaft of the servo motor 5, and the two belt pulleys are sleeved through a transmission belt; therefore, the servo motor 5 outputs power, and the belt transmission mechanism drives the rotating shaft of the choke valve 109 to rotate, so that the opening degree of the choke valve 109 is adjusted and controlled.

In the flow regulating and energy recovering assembly 1, an air inlet at the bottom end of a longitudinal shell is connected with an air outlet of an air compressor 11 through a pipeline. The interface at the top end of the valve cover 102 is connected with the connecting end A of the three-way joint 6 through a negative pressure pipe. The connecting end B of the three-way joint 6 is connected with the negative pressure regulating electromagnetic valve 2 through a negative pressure pipe. The negative pressure regulating electromagnetic valve 2 is connected with a vacuum pump 3 through a pipeline; the negative pressure regulating electromagnetic valve 2 is connected with the controller 4 through a signal line. The connecting end C of the three-way joint 6 is connected with a first pressure sensor 7, and the first pressure sensor 7 measures the air pressure of the negative pressure pipe; the second pressure sensor 8 is fixedly arranged in the transverse shell and is close to the air inlet of the air outlet channel 110 for monitoring the air pressure at the air inlet; the signal line of the second pressure sensor 2 is embedded in the iron core of the conical power generation coil 104, and is led out from the small end of the conical power generation coil 104 through a lead hole 111 on the end face of the outer end of the transverse shell. The signal lines of the first pressure sensor 7 and the second pressure sensor 8 are connected to the controller 4.

In the flow regulation and energy recovery component 1, a lead-out wire of a conical power generation coil 13 is connected with the input end of a super capacitor 9; the output end of the super capacitor 9 is connected with the input end of the power transformation module 10. The output end of the power supply transformation module 10 is connected with the servo motor 5, the controller 4, the negative pressure regulating electromagnetic valve 2 and the vacuum pump 3, and supplies power for electric appliances.

The model of the main chip of the controller 4 is STM32F103RCT6, when the gas flow in the compressor 11 is too large, the controller 4 drives the negative pressure regulating solenoid valve 2 to work through a PWM signal, the conduction time of the negative pressure pipe and the vacuum pump 3 is controlled, meanwhile, the first pressure sensor 7 feeds back a pressure signal in the negative pressure pipe to the controller 4 to form a closed loop, then due to the action of the pressure difference, the plunger 101 moves upwards under the action of the first return spring 106, the redundant gas flow enters the shell 103 through a gap between the plunger 101 and the bottom surface of the longitudinal shell, the conical permanent magnet 14 is pushed to overcome the elastic force of the second return spring group 107, the movement is carried out along the direction of the slide rail 18, and the cutting coil generates electricity; the generated electricity is stored by the super capacitor 9 and supplies power to the servo motor 5, the controller 4, the negative pressure regulating electromagnetic valve 2 and the vacuum pump 3.

Under the condition that the choke valve 109 is fully closed, if the air pressure in the shell 1 is too high, the air in the compressor 11 can be prevented from being discharged, therefore, the second pressure sensor 8 is adopted to monitor the air pressure at the air inlet of the air outlet channel 110 in real time and feed the air pressure back to the main controller 4, the main controller 4 drives the servo motor 5 to rotate, and the servo motor 5 adjusts the opening degree of the choke valve 109 to ensure that redundant air flow in the compressor can be discharged in time.

The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there may be variations in the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.

Claims

1. An anti-surge and energy recovery control device for an aviation piston engine turbocharger is characterized in that: the system comprises a flow regulation and energy recovery assembly, a negative pressure regulation electromagnetic valve, a vacuum pump, a controller, a servo motor, a three-way joint, a first pressure sensor, a second pressure sensor, a super capacitor and a power supply transformation module;

the flow regulation and energy recovery assembly comprises a plunger, a valve cover, a shell, a conical power generation coil, a conical permanent magnet, a first return spring, a second return spring, a sliding rail and a choke valve;

wherein, the shell is provided with a cylindrical transverse shell and a cylindrical L-shaped structural shell of a longitudinal shell; meanwhile, an air outlet channel is designed on the side wall of the transverse shell; a choke valve is arranged at the air outlet of the air outlet channel through a rotating shaft; the plunger piston and the valve cover are coaxially sleeved inside and outside and are coaxially arranged in the longitudinal shell; the top end of the valve cover is provided with an interface communicated with the interior of the valve cover; the plunger is sleeved with a first return spring, and two ends of the first return spring are respectively fixed with the plunger and the valve cover;

2. An anti-surge and energy recovery control device for an aviation piston engine turbocharger as defined in claim 1, wherein: and a lead of the conical power generation coil and a signal wire of the second pressure sensor are embedded into an iron core of the conical power generation coil and are led out from a small end of the conical power generation coil through a lead hole in the end face of the outer end of the transverse shell.

3. An anti-surge and energy recovery control device for an aviation piston engine turbocharger as defined in claim 1, wherein: a sliding block is designed on the side wall at the small end of the conical power generation coil and is installed in a matching way with the sliding rail; the slide rail is axially arranged along the transverse part and fixedly arranged on the inner wall of the transverse shell.

4. An anti-surge and energy recovery control device for an aviation piston engine turbocharger as defined in claim 1, wherein: the inner wall of the outer shell of the flow regulation and energy recovery component is provided with a honeycomb-shaped groove.