CN113236441A - Turbine shaft-fan dual-mode engine and adjusting method thereof - Google Patents
Turbine shaft-fan dual-mode engine and adjusting method thereof Download PDFInfo
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- CN113236441A CN113236441A CN202110467339.2A CN202110467339A CN113236441A CN 113236441 A CN113236441 A CN 113236441A CN 202110467339 A CN202110467339 A CN 202110467339A CN 113236441 A CN113236441 A CN 113236441A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a turboshaft fan bimodal engine and a regulating method thereof, wherein the turboshaft fan bimodal engine has two working modes of a turboshaft and a turbofan, can provide shaft power or thrust for an aircraft, and is suitable for being used as a power device of a short-distance takeoff/vertical landing aircraft, in particular to a short-distance takeoff/vertical landing aircraft with high-speed flight capability; compared with a pure electric power or hybrid power propulsion system, the turboshaft fan dual-mode engine has the characteristics of simple structure and large thrust-weight ratio/power-weight ratio; the fan structure on the rotor blade is adopted to divide the engine into the independent inner duct and the independent outer duct, so that the working state of the inner duct of the engine is not influenced by the working mode, the mature engine core machine and inner duct parts are favorably used, and the development cost and the risk of the engine are reduced.
Description
Technical Field
The invention belongs to the field of aero-engines, and relates to a turboshaft fan dual-mode engine capable of being used as a short-distance takeoff/vertical landing aircraft power device and an adjusting method thereof, in particular to a turboshaft fan dual-mode engine which adopts a fan structure on a rotor blade to divide a fan of a turbofan engine into an inner duct and an outer duct with fixed areas, changes the power requirement of a fan rotor by adjusting the gas flow of the outer duct, and has the advantages that the main output shaft power drives a lift fan or a rotor wing to provide takeoff lift force for an aircraft in a takeoff state, and the thrust force is output in a flat flight state, and an adjusting method thereof.
Background
The existing short take-off/vertical landing aircraft is a novel aircraft combining the advantages of a rotor wing aircraft and a fixed wing aircraft. The aircraft represented by the tilting rotor, the ducted fan and the stalling rotor has the advantages of high cruising efficiency, high flying speed and convenience in taking off and landing, so that the aircraft can deal with more complex application scenes, and is one of research hotspots in the field of aircraft in recent years.
In order to avoid using a gear transmission device with a complex structure and a high failure rate, the small-sized short-distance takeoff/vertical landing aircraft mainly adopts a storage battery as a power source. The range or capacity of such aircraft is very limited, limited by the current low battery power density (about 300W · h/kg). For the aircraft with the takeoff weight of more than 1 ton, the weight of the battery and the motor is in a linear relation with the power, so that the proportion of the weight of the propulsion system is increased, the load capacity of the aircraft is reduced sharply, the flight speed is limited by the overall aerodynamic layout, and the application of the pure electric or oil-electric hybrid propulsion system needs to go through technical attack for a long time.
Disclosure of Invention
The invention provides a novel turboshaft fan dual-mode engine and an adjusting method thereof, aiming at the requirements of a short take-off/vertical landing aircraft, in particular to a short take-off/vertical landing aircraft with high-speed flight capability on a high thrust-weight ratio/power-weight ratio and a high-performance turbine engine.
A turbine axial fan dual-mode engine at least comprises an outer duct, an inner duct, a fan rotor, a core machine, a guider adjustable low-pressure turbine and an adjustable tail jet pipe,
the fan rotor is arranged at the upstream of the core machine, the guider adjustable low-pressure turbine is in transmission connection with the fan rotor through a power output shaft, and the upstream front end of the power output shaft outputs power outwards through a transmission device;
the fan rotor comprises a wheel disc, outer ducted rotor blades, a middle connecting drum barrel and inner ducted rotor blades, wherein the wheel disc is fixedly arranged on the power output shaft, the outer ducted rotor blades are uniformly distributed and fixed on the outer ring of the middle connecting drum barrel along the circumferential direction, the inner ducted rotor blades are uniformly distributed and fixed between the wheel disc and the inner ring of the middle connecting drum barrel along the circumferential direction, the outer ducted rotor blades are positioned in the outer duct, and the inner ducted rotor blades are positioned in the inner duct;
the bypass flow regulating valve comprises a bypass inlet flow regulating valve and a mode selecting valve, wherein the bypass inlet flow regulating valve is arranged at the inlet of the bypass, and the mode selecting valve is arranged at the outlet of the bypass;
the low-pressure turbine with the adjustable guider is arranged in the inner duct and positioned at the downstream of the core machine, and comprises a low-pressure turbine guider with an adjustable area and a low-pressure turbine rotor, wherein the low-pressure turbine guider with the adjustable area is arranged at the upstream of the low-pressure turbine rotor, and the low-pressure turbine rotor is fixedly arranged on the power output shaft;
the adjustable tail nozzle is arranged at the exhaust port of the engine.
Preferably, the core machine is arranged in the inner duct, and the core machine comprises a high-pressure compressor, a combustion chamber and a high-pressure turbine, and the high-pressure turbine is in transmission connection with the high-pressure compressor through a high-pressure turbine shaft.
Preferably, an outer duct inlet adjustable guide vane is further arranged in the outer duct, and the outer duct inlet adjustable guide vane is located at the upstream of the outer duct rotor blade.
Preferably, a fan stator located at the downstream of the outer duct rotor blade is further arranged in the outer duct, the fan stator comprises an outer duct stator blade located in the outer duct, a separation section and an inner duct stator blade located in the inner duct, and the outer duct stator blade and the inner duct stator blade are respectively distributed on an outer ring and an inner ring of the separation section.
Preferably, the turboshaft dual-mode engine of the invention comprises at least a turboshaft engine mode and a turbofan engine mode.
Further, when the engine is in a turboshaft engine mode, the bypass flow regulating valve and the mode selection valve are closed at the same time, the bypass is in a closed state in which only a small amount of airflow passes through, the fan bypass rotor blades basically do not do work on the airflow, one part of the output work of the low-pressure turbine is used for driving the fan rotor, and the other part of the output work is output outwards by a transmission device at the upstream front end of the power output shaft.
Further, to ensure sufficient power output, the throat area of the low pressure turbine nozzle is adjusted to a minimum to increase the low pressure turbine expansion ratio, thereby increasing the effective output power; meanwhile, in order to reduce the residual thrust of the engine, the throat area of the adjustable tail nozzle needs to be adjusted to be the maximum so as to reduce the speed of the airflow and minimize the thrust generated by the airflow. In this operating condition, a small amount of airflow flows through the engine exhaust duct for cooling the engine's outer case, reducing the case and exhaust temperatures, and thereby reducing the engine's infrared radiation intensity.
Further, when the engine is in a turbofan engine mode, the outer duct flow regulating valve and the mode selection valve are fully opened, the outer duct rotor blades of the fan apply work to the gas, and the gas is exhausted from the tail nozzle after being subjected to power application and pressurization through the outer duct rotor blades and the outer duct stator blades.
Further, in order to improve the thrust generated by the airflow, the throat area of the adjustable tail nozzle needs to be adjusted to be minimum, so that the exhaust speed is improved; in order to maintain the low-pressure turbine to work under the high-efficiency working condition, the throat area of the low-pressure turbine guider needs to be adjusted to be the largest, so that the expansion ratio of the low-pressure turbine is reduced, and the work done to the outside is reduced.
Furthermore, the turboshaft fan dual-mode engine also comprises a transition state of mode conversion of the turboshaft fan, wherein at the moment, the outer bypass flow regulating valve and the mode selection valve are synchronously opened according to a preset rule, and meanwhile, the angle of the outer bypass inlet guide blade is adjusted, so that the inlet airflow attack angle of the outer bypass rotor blade of the fan is kept as a negative attack angle (preferably 1-2 degrees), the angle of the outer bypass stator blade of the fan is adjusted along with the adjustment to ensure that the outer bypass airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the surge of the fan caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle is adjusted to be small according to a preset rule, and the throat area of the low-pressure turbine guider is synchronously adjusted to be large.
Furthermore, the turboshaft fan dual-mode engine also comprises a transition state for converting the turboshaft fan into a turboshaft mode, and at the moment, the outer bypass flow regulating valve and the mode selecting valve are synchronously closed according to a preset rule; meanwhile, the angle of the outer duct inlet guide blade is adjusted, so that the attack angle of the inlet airflow of the fan outer duct rotor blade is kept to be a negative attack angle (preferably 1-2 degrees), the angle of the fan outer duct stator blade is adjusted along with the angle of the fan outer duct rotor blade to ensure that the outer duct airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the fan surge caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle is adjusted to be larger according to a preset rule; the throat area of the low-pressure turbine guider is synchronously reduced, in order to prevent the fan from surging, the outer bypass flow regulating valve cannot be completely closed, and the total pressure of the fan outer bypass airflow after being injected by the inner bypass airflow needs to be ensured to be larger than the ambient pressure.
The invention also aims to provide a regulating method of the turboshaft fan dual-mode engine, which is characterized in that when the engine is in a turboshaft engine mode, the outer bypass flow regulating valve and the mode selection valve are closed at the same time, the outer bypass is in a closed state that only a small amount of airflow passes through, the blades of the fan outer bypass rotor basically do not do work on the airflow, one part of the output work of the low-pressure turbine is used for driving the fan rotor, and the other part of the output work is output outwards by a transmission device at the upstream front end of the power output shaft.
Further, to ensure sufficient power output, the throat area of the low pressure turbine nozzle is adjusted to a minimum to increase the low pressure turbine expansion ratio, thereby increasing the effective output power; meanwhile, in order to reduce the residual thrust of the engine, the throat area of the adjustable tail nozzle needs to be adjusted to be the maximum so as to reduce the speed of the airflow and minimize the thrust generated by the airflow. In this operating condition, a small amount of airflow flows through the engine exhaust duct for cooling the engine's outer case, reducing the case and exhaust temperatures, and thereby reducing the engine's infrared radiation intensity.
Further, when the engine is in a turbofan engine mode, the outer duct flow regulating valve and the mode selection valve are fully opened, the outer duct rotor blades of the fan apply work to the gas, and the gas is exhausted from the tail nozzle after being subjected to power application and pressurization through the outer duct rotor blades and the outer duct stator blades.
Further, in order to improve the thrust generated by the airflow, the throat area of the adjustable tail nozzle needs to be adjusted to be minimum, so that the exhaust speed is improved; in order to maintain the low-pressure turbine to work under the high-efficiency working condition, the throat area of the low-pressure turbine guider needs to be adjusted to be the largest, so that the expansion ratio of the low-pressure turbine is reduced, and the work done to the outside is reduced.
Further, when the engine is in a transition state of modal conversion of the turbine axial turbofan, the bypass flow regulating valve and the mode selection valve are synchronously opened according to a preset rule, and simultaneously, the angle of the bypass inlet guide blade is regulated, so that the inlet airflow attack angle of the fan bypass rotor blade is kept as a negative attack angle, the angle of the fan bypass stator blade is regulated along with the adjustment to ensure that the bypass airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the fan surge caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle is adjusted to be small according to a preset rule, and the throat area of the low-pressure turbine guider is synchronously adjusted to be large.
Further, when the engine is in a transition state of converting the turbofan into a turbine shaft mode, the bypass flow regulating valve and the mode selection valve are synchronously closed according to a preset rule; meanwhile, the angle of the outer duct inlet guide blade is adjusted, so that the attack angle of the inlet airflow of the fan outer duct rotor blade is kept as a negative attack angle, the angle of the fan outer duct stator blade is adjusted along with the angle of the fan outer duct stator blade to ensure that the outer duct airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the fan from surging due to the change of external conditions; in the process, the throat area of the adjustable tail nozzle is adjusted to be larger according to a preset rule; the throat area of the low-pressure turbine guider is synchronously reduced, in order to prevent the fan from surging, the outer bypass flow regulating valve cannot be completely closed, and the total pressure of the fan outer bypass airflow after being injected by the inner bypass airflow needs to be ensured to be larger than the ambient pressure.
The invention also aims to provide an aircraft, which is characterized by comprising the turboshaft fan dual-mode engine.
Preferably, the aircraft is a short takeoff/vertical landing aircraft.
Compared with the prior art, the turboshaft fan bimodal engine and the adjusting method thereof have the following characteristics: 1) the turboshaft fan dual-mode engine has two working modes of a turboshaft and a turbofan, can provide shaft power or thrust for an aircraft, and is suitable for being used as a power device of a short-distance takeoff/vertical landing aircraft, in particular to a short-distance takeoff/vertical landing aircraft with high-speed flight capability; 2) compared with a pure electric power or hybrid power propulsion system, the turboshaft fan dual-mode engine has the characteristics of simple structure and large thrust-weight ratio/power-weight ratio; 3) the fan structure on the rotor blade is adopted to divide the engine into the independent inner duct and the independent outer duct, so that the working state of the inner duct of the engine is not influenced by the working mode, the mature engine core machine and inner duct parts are favorably used, and the development cost and the risk of the engine are reduced.
Drawings
FIG. 1 is a schematic structural view of a turboshaft-fan dual-mode engine of the present invention.
The reference numerals are explained below:
the structure comprises an outer duct 100, an inner duct 200, an outer duct flow regulating valve 1, an outer duct inlet flow regulating valve 11, a mode selecting valve 12, an outer duct inlet adjustable guide vane 2, a fan rotor 3, a middle connecting drum 30, outer duct rotor blades 31, inner duct rotor blades 32, a fan stator 4, a separation section 40, outer duct stator blades 41, inner duct stator blades 42, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7, a guider adjustable low-pressure turbine 8, an adjustable tail nozzle 9 and a power output shaft 10
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments, which are part of the present invention, are not all embodiments, and are intended to be illustrative of the present invention and should not be construed as limiting the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in figure 1, the turboshaft fan dual-mode engine at least comprises an outer duct 100, an inner duct 200, a fan rotor 3, a core machine, a guider adjustable low-pressure turbine 8 and an adjustable tail jet pipe 9, wherein the core machine is arranged in the inner duct 200 and comprises a high-pressure compressor 5, a combustion chamber 6 and a high-pressure turbine 7, and the high-pressure turbine 7 is in transmission connection with the high-pressure compressor 5 through a high-pressure turboshaft.
The fan rotor 3 is arranged at the upstream of the core machine, the guider adjustable low-pressure turbine 8 is in transmission connection with the fan rotor 3 through a power output shaft 10, and the upstream front end of the power output shaft 10 outputs power outwards through a transmission device. The fan rotor 3 comprises a wheel disc, an outer duct rotor blade 31, a middle connecting drum 30 and an inner duct rotor blade 32, wherein the wheel disc is fixedly arranged on the power output shaft 10, the outer duct rotor blades 31 are uniformly distributed and fixed on the outer ring of the middle connecting drum 30 along the circumferential direction, the inner duct rotor blades 32 are uniformly distributed and fixed between the wheel disc and the inner ring of the middle connecting drum 30 along the circumferential direction, the outer duct rotor blade 31 is positioned in an outer duct 100, and the inner duct rotor blade 32 is positioned in an inner duct 200.
The outer duct 100 is also preferably provided with an outer duct inlet adjustable guide vane 2, and the outer duct inlet adjustable guide vane 2 is located at the upstream of the outer duct rotor blade 31; the outer duct 100 is also internally provided with a fan stator 4 located at the downstream of the outer duct rotor blade 31, the fan stator 4 comprises an outer duct stator blade 41 located in the outer duct 100, a separation section 40 and an inner duct stator blade 42 located in the inner duct 200, the outer duct stator blade 41 is circumferentially fixed at the outer ring of the separation section 40, and the inner duct stator blade 42 is circumferentially fixed at the inner ring of the separation section 40.
The bypass flow regulating valve 1 comprises a bypass inlet flow regulating valve 11 and a mode selecting valve 12, wherein the bypass inlet flow regulating valve 11 is arranged at the inlet of the bypass 100, and the mode selecting valve 12 is arranged at the outlet of the bypass 100; the low-pressure turbine 8 with adjustable guide device is arranged in the inner duct 200 and is positioned at the downstream of the core machine, and comprises a low-pressure turbine guide device 81 with adjustable area and a low-pressure turbine rotor 82, wherein the low-pressure turbine guide device 81 with adjustable area is arranged at the upstream of the low-pressure turbine rotor 82, and the low-pressure turbine rotor 82 is fixedly arranged on the power output shaft 10; the variable nozzle 9 is arranged at the exhaust port of the engine.
More specifically, as shown in fig. 1, the turboshaft fan dual-mode engine of the present invention is composed of an outer duct flow regulating valve 1, an outer duct inlet adjustable guide vane 2, a fan rotor 3, a fan stator 4, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7, a guider adjustable low-pressure turbine 8, an adjustable tail pipe 9, a power output shaft 10, and the like. The bypass flow regulating valve 1 consists of a bypass inlet flow regulating valve 11 and a mode selecting valve 12; the fan structure is generally referred to as a fan on rotor blades, the fan rotor 3 is composed of an outtake rotor blade 31, an intermediate coupling drum 30 and an intake rotor blade 32, three parts of the fan rotor are driven by the low-pressure turbine 8 and have the same rotating speed; the fan stator 4 consists of an outer ducted stator blade 41, a separation section 40 and an inner ducted stator blade 42; the fan is divided into an inner duct and an outer duct which are independent from each other by the middle connecting drum 30 and the separating section 40 and the related sealing structure, and the corresponding air flow is divided into an inner duct air flow and an outer duct air flow; the low-pressure turbine consists of an area-adjustable low-pressure turbine guide 81 and a low-pressure turbine rotor 82.
The working principle of the turboshaft fan dual-mode engine is as follows:
1. modality of the turboshaft engine: the bypass flow control valve 11 and the mode selection valve 12 are closed, the flow of air passing through the engine bypass is very small, the fan bypass rotor blades do not do work, one part of the output work of the low-pressure turbine is used for driving the fan bypass rotor blades 32, and the other part of the output work is output from the power output shaft 10 to drive the rotor wings or the lift fans of the aircraft, so that the lift is provided for the takeoff or landing of the aircraft. In order to ensure sufficient power output, the area of the low-pressure turbine runner 81 needs to be reduced to increase the low-pressure turbine expansion ratio, thereby increasing the effective output power; meanwhile, in order to reduce the residual thrust of the engine, the throat area of the adjustable tail nozzle 9 needs to be increased, the air flow speed is reduced, and the thrust generated by the air flow is reduced. In this operating condition, a small amount of airflow flows through the engine exhaust duct for cooling the engine's outer case, reducing the case and exhaust temperatures, and thereby reducing the engine's infrared radiation intensity.
2. Turbofan engine modality: the bypass flow regulating valve 11 and the mode selecting valve 12 are opened, the fan bypass rotor blade 31 applies work to the gas, and the gas is exhausted from the tail nozzle after being subjected to work pressurization through the bypass rotor blade 31 and the bypass stator blade 41. In order to improve the thrust, the adjustable tail nozzle 9 needs to be contracted to reduce the throat area, so that the exhaust speed is improved; in order to maintain the low-pressure turbine to work under the high-efficiency working condition, the throat area of the low-pressure turbine guider 81 needs to be increased, the expansion ratio of the low-pressure turbine is reduced, and the work is reduced.
3. Transition state of turbine axial turbofan mode conversion: the outer duct flow regulating valve 11 and the mode selecting valve 12 are opened synchronously according to a preset rule; meanwhile, the angle of the outer duct inlet guide blade 2 is adjusted, so that the attack angle of the inlet airflow of the fan outer duct rotor blade 31 is kept at a negative attack angle of (1-2 degrees), the angle of the fan outer duct stator blade 41 is adjusted along with the angle of the fan outer duct rotor blade to ensure that the outer duct airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the fan surge caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle 9 is adjusted to be small according to a preset rule; the low pressure turbine nozzle 81 throat area is synchronously larger.
4. Transition state of conversion of turbofan to turboshaft mode: the outer duct flow regulating valve 11 and the mode selecting valve 12 are synchronously closed according to a preset rule; meanwhile, the angle of the outer duct inlet guide blade 2 is adjusted, so that the attack angle of the inlet airflow of the fan outer duct rotor blade 31 is kept at a negative attack angle of (1-2 degrees), the angle of the fan outer duct stator blade 41 is adjusted along with the angle of the fan outer duct rotor blade to ensure that the outer duct airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the fan surge caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle 9 is adjusted to be larger according to a preset rule; the throat area of the low pressure turbine nozzle 81 is synchronously reduced. In order to prevent the fan from surging, the outer bypass flow regulating valve 11 cannot be completely closed, and the total pressure of the fan outer bypass airflow injected by the inner bypass airflow needs to be ensured to be greater than the environmental pressure.
The method for adjusting the adjustable structure of a turboshaft fan bimodal engine in each operating state is shown in table 1 below:
TABLE 1
No matter in a stable working mode or in a transition state of mode conversion, before the mode selection valve 12, the air flows of the inner duct and the outer duct of the engine are mutually independent, so that the working states of the air flow of the inner duct and the core engine are not influenced by the working mode of the engine, and the stable working of the inner duct of the engine can be maintained; after the mode selection valve 12, the outer duct airflow and the inner duct airflow are mixed and discharged out of the engine, the high-speed airflow of the inner duct has an injection effect on the outer duct airflow, the minimum opening degree of the outer duct flow regulating valve 11 can be reduced so as to reduce the power consumption of the outer duct fan, and the output power of the state of the turboshaft engine is improved.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (10)
1. A turbine axial fan dual-mode engine at least comprises an outer duct, an inner duct, a fan rotor, a core machine, a guider adjustable low-pressure turbine and an adjustable tail jet pipe,
the fan rotor is arranged at the upstream of the core machine, the guider adjustable low-pressure turbine is in transmission connection with the fan rotor through a power output shaft, and the upstream front end of the power output shaft outputs power outwards through a transmission device;
the fan rotor comprises a wheel disc, outer ducted rotor blades, a middle connecting drum barrel and inner ducted rotor blades, wherein the wheel disc is fixedly arranged on the power output shaft, the outer ducted rotor blades are uniformly distributed and fixed on the outer ring of the middle connecting drum barrel along the circumferential direction, the inner ducted rotor blades are uniformly distributed and fixed between the wheel disc and the inner ring of the middle connecting drum barrel along the circumferential direction, the outer ducted rotor blades are positioned in the outer duct, and the inner ducted rotor blades are positioned in the inner duct;
the bypass flow regulating valve comprises a bypass inlet flow regulating valve and a mode selecting valve, wherein the bypass inlet flow regulating valve is arranged at the inlet of the bypass, and the mode selecting valve is arranged at the outlet of the bypass;
the low-pressure turbine with the adjustable guider is arranged in the inner duct and positioned at the downstream of the core machine, and comprises a low-pressure turbine guider with an adjustable area and a low-pressure turbine rotor, wherein the low-pressure turbine guider with the adjustable area is arranged at the upstream of the low-pressure turbine rotor, and the low-pressure turbine rotor is fixedly arranged on the power output shaft;
the adjustable tail nozzle is arranged at the exhaust port of the engine.
2. The turboshaft dual-modality engine of claim 1, wherein the core engine is disposed within the inner duct and includes a high pressure compressor, a combustion chamber, and a high pressure turbine, the high pressure turbine being drivingly coupled to the high pressure compressor by a high pressure turbine shaft.
3. The turboshaft fan dual-mode engine of claim 1, further comprising an outer duct inlet variable vane disposed within the outer duct, the outer duct inlet variable vane being located upstream of the outer duct rotor blades.
4. The turboshaft fan dual-mode engine according to claim 1, wherein a fan stator is further disposed in the outer duct and located downstream of the outer duct rotor blades, the fan stator includes outer duct stator blades located in the outer duct, a partition section, and inner duct stator blades located in the inner duct, and the outer duct stator blades and the inner duct stator blades are respectively distributed on an outer ring and an inner ring of the partition section.
5. The turboshaft dual-mode engine of claim 1, wherein the engine comprises at least a turboshaft engine mode and a turbofan engine mode.
6. The turboshaft fan dual-mode engine of claim 5, wherein when the engine is in the turboshaft engine mode, the bypass flow control valve and the mode selector valve are closed simultaneously, the bypass is in a state where only a small amount of airflow passes through, the fan bypass rotor blades do not substantially perform work on the airflow, and a portion of the work output by the low-pressure turbine is used to drive the fan rotor and another portion is output externally by a transmission at the upstream front end of the power output shaft.
7. The turboshaft fan dual-mode engine of claim 6, wherein to ensure sufficient power output, the throat area of the low pressure turbine nozzle is adjusted to a minimum to increase the low pressure turbine expansion ratio to increase the effective output power; meanwhile, in order to reduce the residual thrust of the engine, the throat area of the adjustable tail nozzle needs to be adjusted to be the maximum so as to reduce the speed of the airflow and minimize the thrust generated by the airflow. In this operating condition, a small amount of airflow flows through the engine exhaust duct for cooling the engine's outer case, reducing the case and exhaust temperatures, and thereby reducing the engine's infrared radiation intensity.
8. The turboshaft fan dual-mode engine of claim 5, wherein when the engine is in a turbofan engine mode, the bypass flow control valve and the mode select valve are fully open, the fan bypass rotor blades apply work to the gas, and the gas is exhausted from the tailpipe after being pressurized by the bypass rotor blades and the bypass stator blades.
9. The turboshaft fan dual-mode engine of claim 8, wherein to increase the thrust generated by the airflow, the throat area of the variable tailpipe is adjusted to a minimum to increase exhaust velocity; in order to maintain the low-pressure turbine to work under the high-efficiency working condition, the throat area of the low-pressure turbine guider needs to be adjusted to be the largest, so that the expansion ratio of the low-pressure turbine is reduced, and the work done to the outside is reduced.
10. The turboshaft fan dual-mode engine according to claim 5, wherein the turboshaft fan dual-mode engine further comprises a transition state of mode conversion of a turboshaft to a turbofan, at the time, the outer bypass flow regulating valve and the mode selection valve are synchronously opened according to a preset rule, and simultaneously, the angle of the outer bypass inlet guide blade is adjusted, so that the angle of attack of the inlet airflow of the outer bypass rotor blade of the fan is kept at a negative angle of attack (preferably 1-2 °), the angle of the outer bypass stator blade of the fan is adjusted along with the adjustment to ensure that the outer bypass airflow is always in a better working state, and the fan is ensured to have a larger surge margin to prevent the surge of the fan caused by the change of external conditions; in the process, the throat area of the adjustable tail nozzle is adjusted to be small according to a preset rule, and the throat area of the low-pressure turbine guider is synchronously adjusted to be large.
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