CN213016462U - Ram air turbine power generation system - Google Patents
Ram air turbine power generation system Download PDFInfo
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- CN213016462U CN213016462U CN202021859091.1U CN202021859091U CN213016462U CN 213016462 U CN213016462 U CN 213016462U CN 202021859091 U CN202021859091 U CN 202021859091U CN 213016462 U CN213016462 U CN 213016462U
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- ram air
- lubricating oil
- turbine
- precooler
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Abstract
The utility model discloses a ram air turbine power generation system. The system comprises a shutoff valve, a first-stage turbine, a high-speed generator, a second-stage turbine, a controller, an oil lubricating system and a speed regulating valve; the controller is respectively connected with the shutoff valve, the high-speed generator, the electric lubricating oil pump and the speed regulation valve; the first-stage turbine, the high-speed generator and the second-stage turbine are coaxial; the nozzle of the lubricating oil system is positioned near the high-speed generator and the bearing; a shutoff valve is arranged at the inlet end of the first-stage turbine; the outlet end of the first-stage turbine is provided with a speed regulating valve; the controller shell is integrated with a heat dissipation cold plate. The utility model has the advantages of can drive the generator work output electric energy.
Description
Technical Field
The utility model relates to a ram air turbine power generation system.
Background
The ramjet engine of the supersonic aircraft is equipped with high propelling efficiency. However, the ramjet has no rotating machine, and therefore cannot extract shaft work from the ramjet.
Therefore, there is a need to develop a ram air turbine power generation system that can drive a generator to operate to output electrical energy.
Disclosure of Invention
The utility model aims at providing a ram air turbine power generation system, which drives a turbine by using ram air energy obtained by an aircraft in flight to drive a generator to work and output electric energy; simple structure, light weight and high efficiency.
In order to realize the purpose, the technical scheme of the utility model is that: ram air turbine power generation system, its characterized in that: the system comprises a shutoff valve, a first-stage turbine, a high-speed generator, a second-stage turbine, a controller, an oil lubricating system and a speed regulating valve;
the controller is respectively connected with the shutoff valve, the high-speed generator, the electric lubricating oil pump and the speed regulation valve;
the inlet end of the high-speed generator is connected with the first-stage turbine through a bearing, and the outlet end of the high-speed generator is connected with the second-stage turbine through a bearing; the first-stage turbine, the high-speed generator and the second-stage turbine are coaxial;
the nozzle of the lubricating oil system is positioned on the side of the bearing;
a shutoff valve is arranged at the inlet end of the first-stage turbine;
the outlet end of the first-stage turbine is provided with a speed regulating valve;
the controller shell is integrated with a heat dissipation cold plate.
In the technical scheme, the lubricating oil system comprises a lubricating oil tank, a primary oil filter, an electric lubricating oil pump, a secondary oil filter bypass valve and a nozzle;
the outlet end of the oil path of the lubricating oil tank is sequentially connected with the inlet ends of the first-stage oil filter, the electric lubricating oil pump, the second-stage oil filter, the nozzle and the lubricating oil tank;
the secondary oil filter bypass valve is connected with the secondary oil filter in parallel.
In the above technical solution, there are a plurality of the nozzles; a plurality of nozzles are distributed in the housing of the high speed generator.
In the technical scheme, the pressure regulating valve is arranged between the secondary oil filter bypass valve and the lubricating oil tank.
In the above technical solution, the oil system further includes a radiator;
and a first inlet end of the radiator is connected with the electric lubricating oil pump, and a first outlet end of the radiator is connected with the secondary oil filter.
In the above technical solution, the ram air inlet is connected with the inlet end of the shut-off valve;
the ram air outlet is connected with the outlet end of the secondary turbine.
In the technical scheme, the device further comprises a precooler; the first inlet end of the precooler is connected with the ram air inlet, and the first outlet end of the precooler is connected with the inlet end of the shutoff valve;
the outlet end of the second-stage turbine is connected with the second inlet end of the radiator;
the second inlet end of the precooler is connected with the second outlet end of the radiator, and the second outlet end of the precooler is connected with the ram air outlet.
The utility model has the advantages of as follows:
(1) the utility model drives the turbine by utilizing the ram air energy obtained by the aircraft in flight to drive the generator to work and output electric energy; the structure is simple, the weight is light, the efficiency is high, and the method is the best choice for the airborne power supply of the future supersonic aircraft;
(2) the utility model relates to a power supply device used on a supersonic aircraft; the utility model discloses an utilize the ram air energy that the aircraft obtained in flight to drive the turbine and drive the generator electricity generation to required interchange/direct current of aircraft is exported in the controller rectification.
The utility model refines the composition of the lubricating oil system and provides a plurality of choices for the cooling mode of the lubricating oil system; the utility model can adopt a precooler for self-cooling, and can also adopt an airplane with a heat sink for cooling; the weight of the heat sink carried by the airplane can be greatly reduced by adopting the precooler for self-cooling.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural diagram of the present invention.
In FIG. 1, A represents the DC output and B represents the cooling medium in the cold plate; c denotes a cooling medium in the radiator.
In fig. 2, a represents the power output and B represents the cooling medium in the cold plate.
In the figure, 1-shut-off valve, 2-first-stage turbine, 3-precooler, 3.1-precooler first inlet end, 3.2-precooler first outlet end, 3.3-precooler second inlet end, 3.4-precooler second outlet end, 4-lubricating oil tank, 5-first-stage oil filter, 6-electric lubricating oil pump, 7-radiator, 7.1-radiator first inlet end, 7.2-radiator first outlet end, 7.3-radiator second inlet end, 7.4-radiator second outlet end, 8-second-stage oil filter, 9-pressure regulating valve, 10-second-stage oil filter bypass valve, 11-high-speed generator, 12-second-stage turbine, 13-controller, 14-heat dissipation cold plate, 15-lubricating oil system, 16-speed regulation valve, 17-nozzle, 18-bearing, 19-ram air inlet, 20-ram air outlet.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, which are not intended to limit the present invention, but are merely exemplary. While the advantages of the invention will be clear and readily appreciated by the description.
With reference to the accompanying drawings: the ram air turbine power generation system comprises a shutoff valve 1, a first-stage turbine 2, a high-speed generator 11, a second-stage turbine 12, a controller 13, an oil lubricating system 15 and a speed regulating valve 16;
the controller 13 is respectively connected with the shutoff valve 1, the high-speed generator 11, the electric lubricating oil pump 6 and the speed regulation valve 16; the controller adjusts the opening of the speed regulating valve according to the change of the rotating speed and the load of the generator, controls the air flow entering the turbine, and adopts the rotating speed closed loop feedback control to achieve the purpose of stabilizing the rotating speed of the turbine; the first-stage turbine 2, the high-speed generator 11 and the second-stage turbine 12 are coaxial; the ram air enters a first-stage turbine, and then enters a second-stage turbine for further expansion and work after expansion and work; the output work is transmitted to a coaxial generator to convert the shaft work into electric energy; the controller converts the electric energy generated by the generator into electric energy with the quality required by the airplane;
the nozzle 17 of the lubricating oil system 15 is located near the high-speed generator 11 and the bearing 18; the nozzle 17 sprays lubricating oil to the winding end part of the high-speed generator 11 and the bearing 18, lubricates the bearing 17 and dissipates heat to the high-speed generator 11;
a shutoff valve 1 is arranged at the inlet end of the first-stage turbine 2; the outlet end of the first-stage turbine 2 is provided with a speed regulating valve 16; the shutoff valve 1 is used for opening and closing the ram air circulation channel; the opening degree of the speed regulating valve 16 is regulated by a controller to control the air flow entering the turbine;
the controller 13 is characterized in that a shell is integrated with a heat dissipation cold plate 14, electronic components are contained in the controller, the temperature resistance level is low, independent liquid cooling can be adopted, and the heat dissipation cold plate 14 is used for cooling the controller 13.
Further, the lubricating oil system 15 comprises a lubricating oil tank 4, a primary oil filter 5, an electric lubricating oil pump 6, a secondary oil filter 8, a secondary oil filter bypass valve 10 and a nozzle 17;
the outlet end of the oil path of the lubricating oil tank 4 is sequentially connected with the first-stage oil filter 5, the electric lubricating oil pump 6, the second-stage oil filter 8, the nozzle 17 and the inlet end of the lubricating oil tank 4;
the secondary oil filter bypass valve 10 is connected with the secondary oil filter 8 in parallel; the oil system 15 is used to lubricate the bearings 17 and dissipate heat from the high-speed generator 11.
Further, the number of the nozzles 17 is plural; a plurality of nozzles 17 are distributed in the housing of the high-speed generator 11; the nozzle 17 is used for oil injection lubrication and cooling.
Further, a pressure regulating valve 9 is arranged between the secondary oil filter bypass valve 10 and the inlet end of the lubricating oil tank 4, and the pressure regulating valve 9 is used for regulating the pressure of the lubricating oil output by the lubricating oil tank 4 according to actual conditions.
Further, the oil system 15 further includes a radiator 7; the radiator 7 comprises a radiator first inlet end 7.1, a radiator first outlet end 7.2, a radiator second inlet end 7.3 and a radiator second outlet end 7.4; the radiator first inlet end 7.1 and the radiator second outlet end 7.4 are positioned on one side of the radiator 7, and the radiator first inlet end 7.1 and the radiator second outlet end 7.4 are arranged at intervals; the first outlet end 7.2 and the second inlet end 7.3 of the radiator are positioned at the other side of the radiator 7, and the first outlet end 7.2 and the second inlet end 7.3 of the radiator are arranged at intervals;
the first inlet end 7.1 of the radiator is connected with the electric lubricating oil pump 6, and the first outlet end 7.2 of the radiator is connected with the secondary oil filter 8.
Furthermore, the ram air inlet 19 is connected to the inlet end of the shut-off flap 1;
the inlet end of the first-stage turbine 2 is connected with the inlet end of the shutoff valve 1;
a ram air outlet 20 is connected to the outlet end of the secondary turbine 12; the radiator 7 is used to cool the oil in the oil system 15 and/or to cool the air at the outlet of the secondary turbine 12, cooling the precooler 3.
Still further, a precooler 3 is included; the precooler 3 comprises a precooler first inlet end 3.1, a precooler first outlet end 3.2, a cooler second inlet end 3.3 and a precooler second outlet end 3.4; wherein, the first inlet end 3.1 and the second outlet end 3.4 of the precooler are positioned at one side of the precooler 3, and the first inlet end 3.1 and the second outlet end 3.4 of the precooler are arranged at intervals; the first outlet end 3.2 of the precooler and the second inlet end 3.3 of the cooler are positioned at the other side of the precooler 3, and the first outlet end 3.2 of the precooler and the second inlet end 3.3 of the cooler are positioned at intervals in the precooler 3;
the first inlet end 3.1 of the precooler is connected with the ram air inlet 19, and the first outlet end 3.2 of the precooler is connected with the inlet end of the shutoff valve 1; the precooler first inlet end 3.1 is used for cooling the cooled ram air passing through the ram air inlet 19;
the outlet end of the second-stage turbine 12 is connected with the second inlet end 7.3 of the radiator; the radiator is used for cooling lubricating oil circulating in the lubricating oil circuit;
the second precooler inlet end 3.3 is connected with the second radiator outlet end 7.4, and the second precooler outlet end 3.4 is connected with the ram air outlet 20; the precooler 3 serves to cool the high-temperature, high-pressure ram air at the inlet end of the shut-off flap 1 and to discharge the utilized low-pressure ram air through the ram air outlet 20.
The present invention will now be described in detail by way of examples.
Example 1
As shown in fig. 1, the ram air turbine power generation system includes a controller 13, a speed regulation valve 16, a shutoff valve 1, a first-stage turbine 2, a second-stage turbine 12, a high-speed generator 11 and an oil lubrication system 15;
the controller 13 is respectively connected with the shutoff valve 1, the high-speed generator 11, the speed regulating valve 16 and the electric lubricating oil pump 6;
the first-stage turbine 2, the high-speed generator 11 and the second-stage turbine 12 are coaxial;
the nozzle 17 of the lubricating oil system 15 is located near the high-speed generator 11 and the bearing 18;
a shutoff valve 1 is arranged at the inlet end of the first-stage turbine 2;
the outlet end of the first-stage turbine 2 is provided with a speed regulating valve 16
The controller 13 housing integrates a cold plate 14.
The lubricating oil system 15 comprises a lubricating oil tank 4, a primary oil filter 5, an electric lubricating oil pump 6, a secondary oil filter 8, a secondary oil filter bypass valve 10 and a nozzle 17;
the outlet end of the oil path of the lubricating oil tank 4 is sequentially connected with the first-stage oil filter 5, the electric lubricating oil pump 6, the second-stage oil filter 8, the nozzle 17 and the inlet end of the lubricating oil tank 4;
the secondary oil filter bypass valve 10 is connected with the secondary oil filter 8 in parallel.
The number of the nozzles 17 is plural; a plurality of nozzles 17 are distributed in the housing of the high-speed generator 11.
A pressure regulating valve 9 is arranged at the inlet ends of the two-stage oil filter bypass valve 10 and the lubricating oil tank 4.
The oil system 15 further comprises a radiator 7;
the first inlet end 7.1 of the radiator is connected with the electric lubricating oil pump 6, and the first outlet end 7.2 of the radiator is connected with the secondary oil filter 8.
The ram air inlet 19 is connected with the inlet end of the shut-off valve 1;
the inlet end of the first-stage turbine 2 is connected with the inlet end of the shutoff valve 1;
a ram air outlet 20 is connected to the outlet end of the secondary turbine 12.
The cooling in the system of the embodiment adopts the self-carried heat sink of the airplane as the system cooling; wherein, the cooling medium can adopt disposable cooling medium such as fuel, ethanol, water and the like. The controller employs integrated liquid cooling on the aircraft.
In the embodiment, two stages of turbines are adopted and are respectively arranged at two ends of a generator; the generator and the turbine are coaxially and directly driven; the controller is used for controlling the speed regulation valve.
The principle of the embodiment is as follows: the ram air enters a first-stage turbine, and then enters a second-stage turbine for further expansion and work after expansion and work; the output work is transmitted to a coaxial generator to convert the shaft work into electric energy. The controller adjusts the opening of the speed regulating valve according to the change of the rotating speed and the load of the generator, controls the air flow entering the turbine, and adopts the rotating speed closed loop feedback control to achieve the purpose of stabilizing the rotating speed of the turbine; meanwhile, the controller converts the electric energy generated by the generator into electric energy with the quality required by the airplane.
And (4) conclusion: in the embodiment, ram air energy obtained by an aircraft in flight is utilized to drive a turbine to drive a generator to work and output electric energy; the embodiment is the best choice for the airborne power supply of the future supersonic aircraft due to the advantages of simple structure, light weight, high efficiency and the like.
Example 2
As shown in fig. 2, a ram air turbine power generation system, like embodiment 1; the difference lies in that: also comprises a precooler 3; the first inlet end 3.1 of the precooler is connected with the ram air inlet 19, and the first outlet end 3.2 of the precooler is connected with the inlet end of the shutoff valve 1;
the outlet end of the second-stage turbine 12 is connected with the second inlet end 7.3 of the radiator;
the precooler second inlet end 3.3 is connected to the radiator second outlet end 7.4 and the precooler second outlet end 3.4 is connected to the ram air outlet 20.
The present embodiment is a self-cooling ram air turbine power generation system.
The principle of the embodiment is as follows: the hypersonic aircraft has a high flying speed, when the speed reaches 6Ma, the temperature of stagnant ram air in an air inlet channel exceeds 1800K due to viscosity and pneumatic action, and a turbine impeller rotating at a high speed is difficult to bear and needs to be cooled; in the embodiment, the precooler is arranged at the ram air inlet to reduce the inlet air temperature, and the inlet air temperature can be reduced to below 70 ℃ after the inlet air temperature is expanded and cooled by the two-stage turbine, so that the cooling device can be used for cooling the lubricating oil radiator. The air temperature at the outlet of the lubricating oil radiator is still lower, and the lubricating oil radiator can be continuously used for cooling the inlet precooler to realize self-cooling of the system. The output shaft work of the turbine is transmitted to the direct-coupled generator to be converted into electric energy. The controller adjusts the opening of the speed regulating valve according to the change of the rotating speed and the load of the generator, controls the air flow entering the turbine, and adopts the rotating speed closed loop feedback control to achieve the purpose of stabilizing the rotating speed of the turbine; meanwhile, the controller converts the electric energy generated by the generator into electric energy with the quality required by the airplane.
The system of the embodiment adopts precooler self-cooling, wherein the weight of the aircraft carrying heat sink can be greatly reduced by adopting precooler self-cooling of the embodiment.
And (4) conclusion: in the embodiment, ram air energy obtained by an aircraft in flight is utilized to drive a turbine to drive a generator to work and output electric energy; the embodiment has the advantages of simple structure, light weight, high efficiency and the like, and is the best choice for the airborne power supply of the supersonic aircraft in the future; the precooler is arranged in the embodiment, and the self-cooling ram air power generation turbine system for precooling the inlet air can achieve the purpose of active cooling through self-cooling, so that the weight of the aircraft with a cold source is reduced, and the energy efficiency ratio of the aircraft is improved.
Other parts not described belong to the prior art.
Claims (7)
1. Ram air turbine power generation system, its characterized in that: the system comprises a shutoff valve (1), a first-stage turbine (2), a high-speed generator (11), a second-stage turbine (12), a controller (13), an oil lubricating system (15) and a speed regulating valve (16);
the controller (13) is respectively connected with the shutoff valve (1), the high-speed generator (11), the electric lubricating oil pump (6) and the speed regulation valve (16);
the first-stage turbine (2), the high-speed generator (11) and the second-stage turbine (12) are coaxial;
the nozzle (17) of the lubricating oil system (15) is positioned on the side of the bearing (18);
a shutoff valve (1) is arranged at the inlet end of the first-stage turbine (2);
the outlet end of the first-stage turbine (2) is provided with a speed regulating valve (16);
the controller (13) housing integrates a heat sink (14).
2. The ram air turbine power generation system of claim 1, wherein: the lubricating oil system (15) comprises a lubricating oil tank (4), a primary oil filter (5), an electric lubricating oil pump (6), a secondary oil filter (8), a secondary oil filter bypass valve (10) and a nozzle (17);
the outlet end of the oil path of the lubricating oil tank (4) is sequentially connected with the inlet ends of the first-stage oil filter (5), the electric lubricating oil pump (6), the second-stage oil filter (8), the nozzle (17) and the lubricating oil tank (4);
the secondary oil filter bypass valve (10) is connected with the secondary oil filter (8) in parallel.
3. The ram air turbine power generation system of claim 2, wherein: a plurality of the nozzles (17); a plurality of nozzles (17) are distributed in the housing of the high-speed generator (11).
4. The ram air turbine power generation system of claim 3, wherein: a pressure regulating valve (9) is arranged between the secondary oil filter bypass valve (10) and the lubricating oil tank (4).
5. The ram air turbine power generation system of claim 4, wherein: the oil system (15) further comprises a radiator (7);
the first inlet end (7.1) of the radiator is connected with the electric lubricating oil pump (6), and the first outlet end (7.2) of the radiator is connected with the second-stage oil filter (8).
6. The ram air turbine power generation system of claim 5, wherein: the ram air inlet (19) is connected with the inlet end of the shutoff valve (1);
a ram air outlet (20) is connected to the outlet end of the secondary turbine (12).
7. The ram air turbine power generation system of claim 5, wherein: also comprises a precooler (3); the first inlet end (3.1) of the precooler is connected with the ram air inlet (19), and the first outlet end (3.2) of the precooler is connected with the inlet end of the shutoff valve (1);
the outlet end of the secondary turbine (12) is connected with a second inlet end (7.3) of the radiator;
the second inlet end (3.3) of the precooler is connected with the second outlet end (7.4) of the radiator, and the second outlet end (3.4) of the precooler is connected with the ram air outlet (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021859091.1U CN213016462U (en) | 2020-08-31 | 2020-08-31 | Ram air turbine power generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021859091.1U CN213016462U (en) | 2020-08-31 | 2020-08-31 | Ram air turbine power generation system |
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| Publication Number | Publication Date |
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| CN213016462U true CN213016462U (en) | 2021-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021859091.1U Active CN213016462U (en) | 2020-08-31 | 2020-08-31 | Ram air turbine power generation system |
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| CN (1) | CN213016462U (en) |
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- 2020-08-31 CN CN202021859091.1U patent/CN213016462U/en active Active
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