CN214196484U - Interstage rotary detonation variable-circulation turboshaft engine - Google Patents
Interstage rotary detonation variable-circulation turboshaft engine Download PDFInfo
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- CN214196484U CN214196484U CN202120209795.2U CN202120209795U CN214196484U CN 214196484 U CN214196484 U CN 214196484U CN 202120209795 U CN202120209795 U CN 202120209795U CN 214196484 U CN214196484 U CN 214196484U
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Abstract
An interstage rotary detonation variable-circulation turboshaft engine is characterized in that a core machine, a central cavity and a power turbine are sequentially arranged in an inner casing; the central cavity and the power turbine are both connected with a power shaft; a cooling flow path is formed between the inner casing and the outer casing, the inner casing and the outer wall surface of the central cavity form an interstage rotary detonation combustion chamber, and a mixing cooling chamber is formed between the central cavity and the power turbine; the splitter plate is connected with the inner casing to control cooling and air entraining; the oil circuit assembly is controlled to be communicated with the interstage rotary detonation combustor; the igniter is arranged in the interstage rotary detonation combustion chamber and is used for igniting the kerosene-air mixed gas entering the interstage rotary detonation combustion chamber so as to form rotary detonation combustion. The method avoids the derivative problem brought by the scheme that the rotary detonation combustor replaces the isobaric combustor of the turboshaft engine, gives consideration to the high-power requirement of the helicopter in the takeoff stage and the economical target of the helicopter in the cruising stage, and solves the problem that the existing rotary detonation turboshaft engine is difficult to directly detonate and combust when kerosene is adopted as fuel.
Description
Technical Field
The utility model relates to an aeroengine field especially relates to a rotatory detonation of interstage becomes circulation turboshaft engine.
Background
The aviation gas turbine shaft engine (turbo shaft engine for short) is used as a main power device of a helicopter, and the development level of the aviation gas turbine shaft engine has a decisive influence on the comprehensive performance of the helicopter. In recent years, the rotary detonation combustor has attracted wide attention due to the advantages of high heat release rate, small entropy increase, synchronous temperature and pressure increase and the like. The rotary detonation combustor is used for replacing an isobaric combustor of a turboshaft engine, the number of stages of a gas compressor can be reduced, and the power consumption of a compression system is reduced, so that the comprehensive performance of the engine is improved. However, replacing the isobaric combustion chamber of a turboshaft engine with a rotary detonation combustion chamber would inevitably present some problems. For example, the existing rotary detonation combustion chamber is difficult to realize long-time and stable combustion; in the process that the turboshaft engine works from a static state to a 100% rotating speed state, the design difficulty of a rotary detonation combustion chamber in a wide speed range is high; high-frequency pressure pulsation generated by the rotation detonation combustion may affect the stability of the upstream compressor part; the high pressure combustion gases after detonation combustion may cause the turbine internal air system to fail to operate properly, etc.
In addition, most of the existing rotary detonation combustion tests use hydrogen as fuel, but the hydrogen is difficult to store and transport, has small volume energy density and is not suitable for engineering application. In order to realize engineering application, the rotary detonation turboshaft engine must adopt liquid fuel which is easy to store and transport at normal temperature and has large volume energy, such as kerosene. But the activity of kerosene is lower, and the direct detonation difficulty in a rotary detonation combustor is higher. Therefore, the scheme of constructing the rotary detonation turboshaft engine which is more reasonable and feasible in layout, takes kerosene as fuel and is easy to detonate and combust is of practical significance by combining the technical level of the rotary detonation combustion at the present stage.
Disclosure of Invention
An object of the utility model is to solve the above-mentioned problem among the prior art, provide an interstage rotation detonation becomes circulation turboshaft engine, its is rational in infrastructure, compact, both can avoid the derivative problem that rotatory detonation combustion chamber replaces the isobaric combustion chamber scheme of turboshaft engine and brings, can compromise the economic target of helicopter in the high-power demand in the stage of taking off and the stage of cruising again, can solve when current rotatory detonation turboshaft engine adopts kerosene as fuel, be difficult to the technical problem of direct detonation burning.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an interstage rotary detonation variable-circulation turboshaft engine comprises an inner casing, an outer casing, a power shaft, a core engine, a central cavity, a power turbine, a flow distribution plate, an oil way assembly and an igniter; the inner part of the inner casing is sequentially provided with a core machine, a central cavity and a power turbine from front to back; the central cavity and the power turbine are both connected with the power shaft, and are driven by the power turbine to output power outwards; a cooling flow path is formed between the inner casing and the outer casing, an interstage rotary detonation combustion chamber is formed between the inner casing and the outer wall surface of the central cavity, and a mixing cooling chamber is formed between the central cavity and the power turbine; the flow distribution plate is connected with the inner casing and is used for controlling a switch for cooling and air entraining; the oil way assembly is communicated with the interstage rotary detonation combustor in a controlled mode and is used for providing kerosene fuel for the interstage rotary detonation combustor; the igniter is arranged in the interstage rotary detonation combustion chamber and is used for igniting the kerosene-air mixed gas entering the interstage rotary detonation combustion chamber so as to form rotary detonation combustion.
The flow distribution plate comprises a gas compressor cooling air-entraining flow distribution plate and a cooling flow path flow distribution plate, the gas compressor cooling air-entraining flow distribution plate is arranged at the front part of the inner casing, and the cooling flow path flow distribution plate is arranged above the mixing cooling chamber.
The oil way assembly comprises an oil supply pipeline, an atomizing nozzle, a mixing chamber fuel inlet wall surface, a mixing chamber air inlet wall surface and a fuel nozzle; the mixing chamber fuel inlet wall surface and the mixing chamber air inlet wall surface are oppositely arranged in the mixing chamber, and the atomizing nozzle is positioned on one side of the mixing chamber fuel inlet wall surface; the fuel nozzle is positioned below the mixing chamber and extends to the interstage rotary detonation combustion chamber.
And the wall surface of the air inlet of the mixing chamber is provided with small holes for air to pass through.
And the wall surface of the fuel inlet of the mixing chamber is provided with a small hole for kerosene to pass through.
And a plurality of groups of oil circuit assemblies and igniters are uniformly distributed along the circumferential direction of the engine.
And the connection part of the power shaft and the central cavity is tightly sealed by adopting a labyrinth.
The working mode switching of the interstage rotation detonation variable cycle turboshaft engine comprises a high-power and high-oil-consumption mode after an interstage rotation detonation combustion chamber is opened and a low-power and low-oil-consumption mode after the interstage rotation detonation combustion chamber is closed.
The high-power and high-oil-consumption mode after the interstage rotary detonation combustion chamber is started works as follows: when the helicopter is in a takeoff stage and has a large power demand, the oil circuit assembly in the interstage rotary detonation combustion chamber starts to supply oil and ignite for combustion, the splitter plate is opened, the cooling flow path is opened, the interstage rotary detonation combustion chamber starts to work, the output power of the engine is greatly increased, and the oil consumption rate is increased at the same time.
The low-power and low-oil-consumption mode of the interstage rotary detonation combustor after the interstage rotary detonation combustor is closed works as follows: when the helicopter is in a cruising stage, the required power is low, at the moment, the oil way assembly in the interstage rotary detonation combustion chamber interrupts oil supply, the flow distribution plate is closed, the cooling flow path is closed, the interstage rotary detonation combustion chamber stops working and is in a through-flow state, the engine is in a conventional turboshaft engine mode, the output power is low, and the oil consumption rate is obviously reduced.
Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:
1. compare in the scheme that utilizes rotatory detonation combustor to replace the isobaric combustion chamber of turboshaft engine, the utility model provides a rotatory detonation combustor can be similar to afterburning room and only work in short time under the engine maximum speed state as secondary heating part, reduces the operating time and the speed domain scope of rotatory detonation burning by a wide margin, and then reduces the design degree of difficulty of stage rotation detonation combustor, is favorable to realizing the engineering and uses.
2. The utility model can switch between the high-power and high-oil-consumption mode and the low-power and low-oil-consumption mode according to the power requirements of the helicopter in different flight stages; specifically, the helicopter works in a high-power and high-oil-consumption mode in the takeoff stage; and the helicopter works in a low-power and low-oil-consumption mode in a cruising stage.
3. The utility model discloses steerable isobaric combustion chamber carries out the rich oil burning, makes partial kerosene be heated and takes place the schizolysis, produces the higher gas composition of activity, is favorable to the ignition detonation of kerosene in the rotatory detonation combustion chamber of interstage to solve when current rotatory detonation turboshaft engine adopts kerosene as the fuel, be difficult to the technical problem of direct detonation burning.
4. The utility model basically does not need to change the structure of the core machine; the throat sections of the upstream turbine stator and the downstream turbine stator can restrict the detonation waves; the design of the turbine air system can also be done directly by bleeding air from the compressor.
5. The mixing chamber air inlet wall surface and the mixing chamber fuel oil inlet wall surface are provided with small holes, so that the two wall surfaces can decelerate air/kerosene, premixing of the air/kerosene and the kerosene in the mixing chamber is facilitated, and detonation and stable combustion of the rotary detonation combustor are facilitated.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is an enlarged schematic view of the oil passage assembly.
Fig. 3 is a schematic circumferential position diagram of the oil passage assembly.
FIG. 4 is a schematic view of the mixing chamber fuel (air) inlet wall.
Fig. 5 is an enlarged schematic view of a labyrinth sealing structure.
Reference numerals: the method comprises the following steps of 1, 2, 3, a core machine, 31, 32 and isobaric combustion chambers, 33 gas turbines, 4-stage rotary detonation combustion chambers, 5 mixing cooling chambers, 6 power turbines, 7 spray pipes, 8 power shafts, 9 air inlet channels, 10 compressor cooling bleed air splitter plates, 11 high-pressure rotor shafts, 12 cooling flow paths, 13 oil way assemblies, 131 oil supply pipelines, 132 atomizing nozzles, 133 mixing chamber fuel inlet wall surfaces, 134 mixing chambers, 135 mixing chamber air inlet wall surfaces, 136 fuel nozzles, 14 igniters, 15 cooling flow path splitter plates, 16 central cavities and 17 labyrinth seals.
Detailed Description
In order to make the technical problem, technical solution and beneficial effects to be solved by the present invention clearer and more obvious, the following description is made in detail with reference to the accompanying drawings and embodiments.
As shown in fig. 1, the present embodiment includes an inner casing 1, an outer casing 2, a power shaft 8, a core engine 3, a central cavity 16, a power turbine 6, a splitter plate, an oil path assembly 13, and an igniter 14.
The inner part of the inner casing 1 is sequentially provided with a core machine 3, a central cavity 16 and a power turbine 6 from front to back; the central cavity 16 and the power turbine 6 are both connected with the power shaft 8 and are driven by the power turbine 6 to output power outwards.
The core machine 3 comprises a compressor 31, an isobaric combustion chamber 32 and a gas turbine 33, wherein the compressor 31 and the gas turbine 33 are connected by a high-pressure rotor shaft 11 and rotate synchronously.
A cooling flow path 12 is formed between the inner casing 1 and the outer casing 2, an interstage rotary detonation combustion chamber 4 is formed between the inner casing 1 and the outer wall surface of a central cavity 16, and a blending cooling chamber 5 is formed between the central cavity 16 and the power turbine 6.
The flow distribution plate is connected with the inner casing 1 and is used for controlling a switch for cooling and air entraining; specifically, the flow dividing plates comprise a compressor cooling bleed air flow dividing plate 10 and a cooling flow path flow dividing plate 15, the compressor cooling bleed air flow dividing plate 10 is arranged at the front part of the inner casing 1, and the cooling flow path flow dividing plate 15 is arranged above the blending cooling chamber 5.
The oil circuit assembly 13 is communicated with the interstage rotary detonation combustor 4 in a controlled mode and is used for providing kerosene fuel for the interstage rotary detonation combustor 4; specifically, the oil path assembly 13 includes an oil supply line 131, an atomizer 132, a blending chamber fuel inlet wall 133, a blending chamber 134, a blending chamber air inlet wall 135, and a fuel nozzle 136; the blending chamber fuel inlet wall surface 133 and the blending chamber air inlet wall surface 135 are oppositely arranged in the blending chamber 134, and the atomizing nozzle 132 is positioned on one side of the blending chamber fuel inlet wall surface 133; the fuel nozzle 136 is positioned below the blending chamber 134 and extends to the interstage rotary detonation combustion chamber 4. More specifically, the mixing chamber air inlet wall 135 is provided with small holes for the passage of air. The mixing chamber fuel inlet wall 133 is provided with small holes for kerosene to pass through.
The igniter 14 is arranged in the interstage rotary detonation combustion chamber 4 and is used for igniting the kerosene-air mixed gas entering the interstage rotary detonation combustion chamber 4 so as to form rotary detonation combustion.
The utility model discloses can switch between 2 working modes according to the power demand of the different flight stages of helicopter, do respectively: the high-power and high-oil-consumption mode of the interstage rotary detonation combustor after the interstage rotary detonation combustor is started and the low-power and low-oil-consumption mode of the interstage rotary detonation combustor after the interstage rotary detonation combustor is closed.
Referring to fig. 1, when the helicopter is in the stage of taking off great to the power demand, the utility model discloses with high-power, the high oil consumption mode after the rotatory detonation combustion chamber of work in stage is opened, concrete process is as follows: the incoming air enters the engine from the air inlet 9 and is compressed by the air compressor 31, and the pressure and the temperature are improved; the compressed air enters an isobaric combustion chamber 32 for isobaric rich oil combustion, and part of kerosene is heated and cracked in the rich oil combustion process to generate active gases such as hydrogen, ethylene, propylene and the like; the burnt high-temperature gas impacts to drive the gas turbine 33 to rotate to do work so as to maintain the continuous operation of the gas compressor 31; then, gas at the outlet of the gas turbine 33 enters the interstage rotary detonation combustor 4 and is mixed with kerosene/air mixed gas sprayed by the oil way assembly 13, and the mixed gas is ignited by the igniter 14 under the catalytic action of active gas to form rotary detonation combustion; meanwhile, the compressor cooling bleed air splitter plate 10 and the cooling flow path splitter plate 15 are opened, part of cold air flows into the blending cooling chamber 5 through the cooling flow path 12 and is blended and cooled with high-temperature gas at the outlet of the interstage rotary detonation combustor 4, so that the temperature of the gas entering the power turbine 6 is not higher than the material limit temperature; the power turbine 6 starts to rotate to apply work and drive the power shaft 8 to output power outwards after being impacted by mixed and cooled gas, and finally the gas is discharged outwards through the spray pipe 7. It is added that the cooling flow path splitter plate 15 can be controlled to be in different opening positions according to different outlet gas temperatures of the interstage rotary detonation combustor 4 and the material limiting temperature of the power turbine 6 so as to adjust the cooling air flow entering the blending cooling chamber 5.
Referring to fig. 1, when the helicopter is in the stage of cruising and is less to the power demand, the utility model discloses low-power, the low oil consumption mode after will working and close at the rotatory detonation combustion chamber between grades, specific process is as follows: the incoming air enters the engine from the air inlet 9 and is compressed by the air compressor 31, and the pressure and the temperature are improved; the compressed air enters the isobaric combustion chamber 32 to perform isobaric lean oil combustion so as to improve the combustion efficiency, and the combusted high-temperature gas impacts to drive the gas turbine 33 to rotate to do work so as to maintain the continuous operation of the gas compressor 31; meanwhile, the oil supply of the oil circuit assembly 13 is interrupted, the interstage rotary detonation combustor 4 stops working and is in a through-flow state, the air compressor cools the air-entraining splitter plate 10 and the cooling flow path splitter plate 15 are also in a closed state, high-temperature gas at the outlet of the gas turbine 33 directly impacts the power turbine 6 after passing through the interstage rotary detonation combustor 4, the power turbine 6 starts to rotate to do work and drive the power shaft 8 to output power outwards, and finally the gas is discharged outwards through the spray pipe 7.
Referring to fig. 2 to 4, the present invention provides an oil circuit assembly 13 and an igniter 14 along the circumferential uniform distribution 6 of the engine, so as to facilitate the smooth detonation and stable combustion of the interstage rotary detonation combustor 4. Kerosene is supplied through the oil supply line 131, atomized by the atomizing nozzle 132 and reduced in speed after flowing into the blending chamber 134 through the small holes in the fuel inlet wall 133 of the blending chamber; at the same time, a small portion of the air in the cooling flow path 12 enters the blending chamber 134 after being decelerated by the blending chamber air inlet wall 135; in the mixing chamber 134, the low-speed kerosene and the low-speed air are preliminarily mixed and then are sprayed out through the fuel nozzle 136; the ejected mixed gas is further fully mixed with the inflow gas in the interstage rotary detonation combustion chamber 4, and then is ignited by the igniter 14 to form rotary detonation combustion.
Fig. 5 is a 17 enlargements of labyrinth seal structure, the utility model discloses when being in operating condition, power shaft 8 also will be in high-speed rotation state under power turbine 6's drive, and power shaft 8 adopts the labyrinth seal 17 with the junction of center chamber 16, has both satisfied the high-speed rotatory requirement of power shaft 8, also can prevent that gas from leaking to center chamber 16 is interior.
The utility model discloses in, work as when the engine work is in the high-power mode after the rotatory detonation combustion chamber of interstage opens, control isobaric combustion chamber in the engine carries out the rich oil burning, makes partial kerosene be heated and takes place the schizolysis, produces compositions such as the higher hydrogen of activity, ethylene, propylene. The active ingredients are beneficial to ignition and detonation of kerosene after entering the interstage rotary detonation combustor, so that the technical problem that the existing rotary detonation turboshaft engine is difficult to directly detonate and combust when the kerosene is adopted as fuel is solved. When the engine works in a conventional turboshaft engine mode after the interstage rotary detonation combustion chamber is closed, the isobaric combustion chamber in the engine is controlled to recover lean oil combustion, so that the combustion efficiency is improved, and the further reduction of the fuel consumption rate of the engine is facilitated.
Claims (7)
1. An interstage rotary detonation variable cycle turboshaft engine, characterized in that: the device comprises an inner casing, an outer casing, a power shaft, a core machine, a central cavity, a power turbine, a flow distribution plate, an oil circuit assembly and an igniter; the inner part of the inner casing is sequentially provided with a core machine, a central cavity and a power turbine from front to back; the central cavity and the power turbine are both connected with the power shaft, and are driven by the power turbine to output power outwards; a cooling flow path is formed between the inner casing and the outer casing, an interstage rotary detonation combustion chamber is formed between the inner casing and the outer wall surface of the central cavity, and a mixing cooling chamber is formed between the central cavity and the power turbine; the flow distribution plate is connected with the inner casing and is used for controlling a switch for cooling and air entraining; the oil way assembly is communicated with the interstage rotary detonation combustor in a controlled mode and is used for providing kerosene fuel for the interstage rotary detonation combustor; the igniter is arranged in the interstage rotary detonation combustion chamber and is used for igniting the kerosene-air mixed gas entering the interstage rotary detonation combustion chamber so as to form rotary detonation combustion.
2. The interstage rotary detonation variable cycle turboshaft engine as claimed in claim 1, wherein: the flow distribution plate comprises a gas compressor cooling air-entraining flow distribution plate and a cooling flow path flow distribution plate, the gas compressor cooling air-entraining flow distribution plate is arranged at the front part of the inner casing, and the cooling flow path flow distribution plate is arranged above the mixing cooling chamber.
3. The interstage rotary detonation variable cycle turboshaft engine as claimed in claim 1, wherein: the oil way assembly comprises an oil supply pipeline, an atomizing nozzle, a mixing chamber fuel inlet wall surface, a mixing chamber air inlet wall surface and a fuel nozzle; the mixing chamber fuel inlet wall surface and the mixing chamber air inlet wall surface are oppositely arranged in the mixing chamber, and the atomizing nozzle is positioned on one side of the mixing chamber fuel inlet wall surface; the fuel nozzle is positioned below the mixing chamber and extends to the interstage rotary detonation combustion chamber.
4. An interstage rotary detonation variable cycle turboshaft engine as claimed in claim 3, wherein: and the wall surface of the air inlet of the mixing chamber is provided with small holes for air to pass through.
5. An interstage rotary detonation variable cycle turboshaft engine as claimed in claim 3, wherein: and the wall surface of the fuel inlet of the mixing chamber is provided with a small hole for kerosene to pass through.
6. The interstage rotary detonation variable cycle turboshaft engine as claimed in claim 1, wherein: and a plurality of groups of oil circuit assemblies and igniters are uniformly distributed along the circumferential direction of the engine.
7. The interstage rotary detonation variable cycle turboshaft engine as claimed in claim 1, wherein: and the connection part of the power shaft and the central cavity is tightly sealed by adopting a labyrinth.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120209795.2U CN214196484U (en) | 2021-01-26 | 2021-01-26 | Interstage rotary detonation variable-circulation turboshaft engine |
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| CN202120209795.2U CN214196484U (en) | 2021-01-26 | 2021-01-26 | Interstage rotary detonation variable-circulation turboshaft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115218224A (en) * | 2022-07-29 | 2022-10-21 | 西安热工研究院有限公司 | Cooling structure suitable for pulse detonation combustion chamber |
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2021
- 2021-01-26 CN CN202120209795.2U patent/CN214196484U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115218224A (en) * | 2022-07-29 | 2022-10-21 | 西安热工研究院有限公司 | Cooling structure suitable for pulse detonation combustion chamber |
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