CN113309633B - Engine with variable circulation and stepless speed change driving fan combination layout - Google Patents

Engine with variable circulation and stepless speed change driving fan combination layout Download PDF

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Publication number
CN113309633B
CN113309633B CN202110584548.5A CN202110584548A CN113309633B CN 113309633 B CN113309633 B CN 113309633B CN 202110584548 A CN202110584548 A CN 202110584548A CN 113309633 B CN113309633 B CN 113309633B
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fan
engine
rotating speed
turbine
stepless speed
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CN113309633A (en
Inventor
朱俊强
董旭
张燕峰
卢新根
屈骁
阳诚武
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Institute of Engineering Thermophysics of CAS
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Institute of Engineering Thermophysics of CAS
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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
    • F02K3/06—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 with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • 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
    • F02K1/15—Control or regulation
    • F02K1/16—Control or regulation conjointly with another control
    • F02K1/165—Control or regulation conjointly with another control with air intake control
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses an engine with variable circulation and stepless speed change driving fan combination layout, which is characterized in that a fan is in transmission connection with a content core machine by using a stepless speed changer, the tail spray pipe is set to be an adjustable tail spray pipe with an adjustable nozzle area, the stepless speed changer is used for independently adjusting the rotating speed of the fan, so that the rotating speed of the fan is separated from the rotating speed of the content core machine, the content core machine is enabled to independently operate in the highest efficiency state, the rotating speed of the fan is continuously changed by the stepless speed changer, and the continuous adjustment of the thrust of the engine is realized by matching with the continuously adjustable nozzle area of the adjustable tail spray pipe, so as to adapt to different working conditions of an aircraft.

Description

Engine with variable circulation and stepless speed change driving fan combination layout
Technical Field
The invention belongs to the technical field of light-duty power gas turbine engines, relates to a light-duty power engine, and particularly relates to a light-duty power gas turbine engine with a combined layout of variable-cycle and infinitely variable-speed driving fans, which has the characteristics of high efficiency and low oil consumption rate under the condition of meeting the power requirements of multiple working conditions of an unmanned aerial vehicle.
Background
With the expansion of the operating range of the unmanned aerial vehicle from high subsonic speed to supersonic speed, the requirements of the engine on the matching of thrust, oil consumption rate, size and the like with the requirements of multiple working conditions in a flight envelope line in the design process are required. The engines with which unmanned aircraft are equipped are generally turbojet engines or turbofan engines, the former having high fuel consumption but capable of providing the aircraft with high flight speeds, the latter having higher efficiency and lower fuel consumption at relatively low speeds. Under the multiple working conditions of high-speed cruising, low-speed reconnaissance and the like of the unmanned aerial vehicle, the requirements on the engine are mutually conflicting, and the independent turbojet engine or turbofan engine can hardly meet the thrust requirement of the multiple working conditions and also has high efficiency and low oil consumption rate.
Disclosure of Invention
According to the problems, the invention provides a variable-cycle and stepless-speed-change driving fan combined layout engine aiming at a light-power gas turbine engine by combining the characteristics of power requirements of an unmanned aerial vehicle under multiple working conditions, a fan is in transmission connection with a culvert core machine by using a stepless speed changer, the tail spray pipe is arranged into an adjustable tail spray pipe with an adjustable nozzle area, the stepless speed changer is used for independently adjusting the rotating speed of the fan, so that the rotating speed of the fan is separated from the rotating speed of the culvert core machine, the culvert core machine independently operates in the highest-efficiency state, the rotating speed of the fan is continuously changed by the stepless speed changer, the continuously adjustable nozzle area of the adjustable tail spray pipe is matched, the continuous adjustment of the thrust of the engine is realized, the engine is adapted to different working conditions of the aircraft, and the characteristics of high efficiency and low oil consumption rate are achieved under the power requirements of the unmanned aerial vehicle under multiple working conditions, and the stable operation of the engine under the working conditions of subsonic speed and supersonic speed can be ensured.
In order to solve the technical problem, the invention adopts the technical scheme that:
an engine with variable circulation and stepless speed change driving fan combination layout comprises an inner culvert core machine, a fan, an inner duct, an outer duct and a tail spray pipe, wherein the inner culvert core machine comprises a gas compressor, a combustion chamber and a turbine, the turbine is in transmission connection with the gas compressor through a transmission shaft, the fan is arranged at the upstream of the gas compressor, the tail spray pipe is arranged at the downstream of the turbine, and air enters the tail spray pipe through the inner duct and the outer duct,
the fan is in transmission connection with a transmission shaft of the content core machine through a stepless speed changer,
the tail spray pipe is an adjustable tail spray pipe with an adjustable nozzle area,
the stepless speed changer is used for independently adjusting the rotating speed of the fan, so that the rotating speed of the fan is separated from the rotating speed of the inner core machine, the inner core machine independently operates in the highest efficiency state, the rotating speed of the fan is continuously changed through the stepless speed changer, and the continuous adjustment of the thrust of the engine is realized by matching with the continuously adjustable nozzle area of the adjustable tail nozzle, so that the aircraft can adapt to different working conditions.
Another object of the invention is to provide an aircraft characterized in that it comprises an engine according to the invention as described above.
Another object of the present invention is to provide a method for designing the engine, wherein the method at least includes the steps of:
SS1. inputting flight conditions, engine data and component characteristics;
SS2, interpolating each part (a fan, an air compressor and a turbine) of the engine by using the rotating speed of the engine and a beta line as coordinates to obtain a characteristic diagram meeting the flight requirement;
SS3, selecting the connotation rotating speed and the transmission ratio;
SS4, selecting a fan beta line as an external iteration cycle parameter, wherein the beta line is a working envelope line (a linear or parabolic line between a blockage line and a surge line, and a certain distance exists between every two beta lines, so that the beta line has no physical significance, but an alternative coordinate system is introduced by adding the beta line, so that the beta line can be rapidly positioned to a unique working condition point during design and is a common tool during design;
SS5, obtaining a fan characteristic diagram and extracting mass flow, pressure ratio and efficiency;
SS6, calculating the characteristics of the culvert;
SS7, reading the characteristics of the compressor;
SS8, selecting the total temperature of the front inlet of the turbine as an inner loop iteration parameter;
SS9. calculating a combustion chamber characteristic;
SS10. calculating turbine characteristics;
SS11, iterating the content circulation to ensure the conservation of content quality;
and SS12, iterating an inlet and outlet loop to ensure conservation of inlet and outlet quality.
Compared with the prior art, the variable-cycle and stepless speed change driving fan layout suitable for the light power gas turbine engine has the following characteristics: 1) the efficiency is high: the inner core machine independently operates in an optimal efficiency state, and the efficiency is basically not lost in the thrust changing process of the engine. 2) The thrust can be continuously adjusted: by adjusting the transmission ratio of the continuously variable transmission and the area of the nozzle, the thrust of the engine can be continuously adjusted. 3) The oil consumption rate is low: the thrust is provided by the connotation and the connotation together, and the defect of high oil consumption rate in the turbojet engine is avoided. 4) The structure is relatively simple: compared with a gear-driven fan, the stepless speed change driven fan is simpler in structure, high in reliability and strong in flexibility. Through model verification, compared with an engine without the configuration, the light-duty power gas turbine engine with the combined layout of the variable-cycle and infinitely variable-speed driving fans, which is provided by the invention, has the advantages that the oil consumption can be reduced by 20%, the thrust is increased by 20-35%, and the stable operation of the engine under the working conditions of subsonic speed and supersonic speed can be ensured.
Drawings
FIG. 1 is a schematic view of a conventional turbojet engine.
FIG. 2 is a schematic view of a conventional turbofan engine.
FIG. 3 is a schematic diagram of an engine with a variable cycle and infinitely variable drive fan combination layout according to the present invention.
FIG. 4 is a schematic diagram of a continuously variable transmission in which (a) a low ratio condition; (b) a high ratio regime.
FIG. 5 is a schematic representation of gear ratios versus fan operating line.
FIG. 6 is a schematic diagram showing the relationship between the nozzle area and the fan operating line.
In the drawings, the reference numerals are explained as follows:
1-compressor, 2-combustion chamber, 3-turbine, 4-fan, 5-stepless speed changer, 6-adjustable nozzle, 7-shaft connected with compressor, 8-driving wheel set, 9-shaft connected with fan and 10-driven wheel set
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.
The invention provides a light-power gas turbine engine with a variable-cycle and infinitely variable-speed driving fan combined layout, aiming at the light-power gas turbine engine, combining the characteristic of power requirements of an unmanned aerial vehicle under multiple working conditions. The power demand of satisfying unmanned vehicles multiplex condition has the characteristics of high efficiency and low oil consumption concurrently.
Fig. 1 is a schematic view of a conventional turbojet engine. As shown in fig. 1, the core main components of a conventional turbojet engine include a compressor 1, a combustion chamber 2 and a turbine 3, the turbine 3 is in transmission connection with the compressor 1 through a transmission shaft, high-temperature gas generated by the combustion chamber 2 pushes the turbine 3 to rotate, and the turbine 3 drives the compressor 1 through the transmission shaft. Generally, the engine with the configuration can provide the aircraft with higher flying speed, but has higher fuel consumption rate, and is suitable for the high-speed cruising stage of the unmanned aircraft.
FIG. 2 is a schematic view of a conventional turbofan engine. As shown in fig. 2, the conventional turbofan engine includes, in addition to main components of the turbojet engine, namely, a compressor 1, a combustion chamber 2, and a turbine 3, which constitute a core engine, a fan 4 is further added, the fan 4 is directly disposed at the front end of a transmission shaft and is provided with an inner duct and an outer duct, and a tail nozzle pipe with a fixed nozzle area is disposed at the downstream tail of the core engine. The air enters the tail nozzle through the inner duct and the outer duct under the driving of the fan 4. The engine with the configuration can provide high efficiency and relatively large thrust for the aircraft, but cannot provide high speed for the aircraft, and is suitable for the low-speed reconnaissance stage of the unmanned aircraft. In such an engine configuration, when the unmanned aerial vehicle performs a transition between high-speed flight and low-speed flight phases, if only the rotation speed of the propeller shaft is changed, efficiency is reduced.
FIG. 3 is a schematic diagram of an engine with a combination of variable cycle and infinitely variable speed drive fans according to the present invention. As shown in fig. 3, compared with the conventional turbofan engine (as shown in fig. 2), the gas turbine engine with the combined layout of the variable-cycle and infinitely variable-speed driving fans of the invention has the advantages that the infinitely variable transmission 5 is added between the compressor 1 and the fan 4, and the outlet of the exhaust nozzle is changed into the adjustable exhaust nozzle 6, namely, the fan 4 is in transmission connection with the transmission shaft of the internal core engine through the infinitely variable transmission 5, and the exhaust nozzle is the adjustable exhaust nozzle 6 with the adjustable nozzle area. The continuously variable transmission 5 is used for independently adjusting the rotating speed of the fan 4, so that the rotating speed of the fan 4 can be separated from the rotating speed of the content core machine, and the content core machine can independently operate in the highest efficiency state. The rotating speed of the fan 4 is continuously changed through the continuously variable transmission 5, and the continuous adjustment of the thrust of the engine is realized by matching with the continuously adjustable nozzle area of the adjustable tail jet pipe 6, so that the continuously adjustable jet nozzle is suitable for different working conditions of an aircraft. In the evaluation of the maximum efficiency, the transmission ratio, the nozzle area and the connotation speed are the main parameters affecting the efficiency.
Compared with a gear-driven fan with a fixed transmission ratio, the stepless speed changer-driven fan has the advantages of simple structure, few parts and high reliability, and the basic structure of the stepless speed changer is shown in fig. 4. The stepless speed changer can realize continuous change of transmission ratio without being limited by gear transmission ratio, can realize continuous change of thrust by matching with an adjustable nozzle, and has high flexibility, fig. 4 shows a working schematic diagram of the stepless speed changer respectively showing two states of minimum transmission ratio and maximum transmission ratio, wherein, (a) shows a state of small transmission ratio, (b) shows a state of large transmission ratio, 5 shows the stepless speed changer, 7 shows a shaft connected with a gas compressor, 8 shows a driving wheel group, 9 shows a shaft connected with a fan, and 10 shows a driven wheel group. Because the connotation in the process is always operated at the maximum efficiency and rotation speed, the efficiency is basically not lost along with the change of the thrust.
FIG. 5 is a continuously variable transmission ratio versus fan characteristic with the fan operating line progressively approaching the stall line as the ratio increases. FIG. 6 is a graph of nozzle area versus fan characteristic, with the fan operating line progressively approaching the stall line as the nozzle area decreases. The combination of the two can basically enable the fan to independently operate at any operating point in the stable operating envelope.
For the variable-cycle and stepless-drive fan combined layout engine, the design is carried out according to a fixed transmission ratio. Since the continuously variable transmission can achieve a continuous change in gear ratio, multiple stages of calculation are required to derive the overall performance of the engine. The design method and the process are as follows:
SS1. inputting flight conditions, engine data and component characteristics;
SS2, interpolating each part (a fan, an air compressor and a turbine) of the engine by using the rotating speed of the engine and a beta line as coordinates to obtain a characteristic diagram meeting the flight requirement;
SS3, selecting the connotation rotating speed and the transmission ratio;
SS4, selecting a fan beta line as an external iteration cycle parameter, wherein the beta line is a working envelope line (a linear or parabolic line between a blockage line and a surge line, and a certain distance exists between every two beta lines, so that the beta line has no physical significance, but an alternative coordinate system is introduced by adding the beta line, so that the beta line can be rapidly positioned to a unique working condition point during design and is a common tool during design;
SS5, obtaining a fan characteristic diagram and extracting mass flow, pressure ratio and efficiency;
SS6, calculating the characteristics of the culvert;
SS7, reading the characteristics of the compressor;
SS8, selecting the total temperature of the front inlet of the turbine as an inner loop iteration parameter;
SS9. calculating a combustion chamber characteristic;
SS10. calculating turbine characteristics;
SS11, iterating the content circulation to ensure the conservation of content quality;
and SS12, iterating an inlet and outlet loop to ensure conservation of inlet and outlet quality.
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 (2)

1. An engine with variable circulation and stepless speed change driving fan combination layout comprises an inner culvert core machine, a fan, an inner duct, an outer duct and a tail spray pipe, wherein the inner culvert core machine comprises a gas compressor, a combustion chamber and a turbine, the turbine is in transmission connection with the gas compressor through a transmission shaft, the fan is arranged at the upstream of the gas compressor, the tail spray pipe is arranged at the downstream of the turbine, and air enters the tail spray pipe through the inner duct and the outer duct,
the fan is in transmission connection with a transmission shaft of the content core machine through a stepless speed changer,
the tail spray pipe is an adjustable tail spray pipe with an adjustable nozzle area,
the stepless speed changer is used for independently adjusting the rotating speed of the fan, so that the rotating speed of the fan is separated from the rotating speed of the inner core machine, the inner core machine independently operates in the highest efficiency state, the rotating speed of the fan is continuously changed through the stepless speed changer, and the continuous adjustment of the thrust of the engine is realized by matching with the continuously adjustable nozzle area of the adjustable tail nozzle, so as to adapt to different working conditions of the aircraft;
the engine is designed according to the following steps:
SS1. inputting flight conditions, engine data and component characteristics;
SS2, interpolating a fan, a gas compressor and a turbine in the engine by using the rotating speed of the engine and a beta line as coordinates to obtain a characteristic diagram meeting the flight requirement;
SS3, selecting the connotation rotating speed and the transmission ratio;
SS4, selecting a beta line of the fan as an external iteration cycle parameter, wherein the beta line is a working envelope;
SS5, obtaining a fan characteristic diagram and extracting mass flow, pressure ratio and efficiency;
SS6, calculating the characteristics of the culvert;
SS7, reading the characteristics of the compressor;
SS8, selecting the total temperature of the front inlet of the turbine as an inner loop iteration parameter;
SS9. calculating a combustion chamber characteristic;
SS10. calculating turbine characteristics;
SS11, iterating the content circulation to ensure the conservation of content quality;
and SS12, iterating an inlet and outlet loop to ensure conservation of inlet and outlet quality.
2. An aircraft, characterized in that it comprises an engine according to claim 1.
CN202110584548.5A 2021-05-27 2021-05-27 Engine with variable circulation and stepless speed change driving fan combination layout Active CN113309633B (en)

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CN114017201B (en) * 2021-11-16 2023-04-07 中国航发沈阳发动机研究所 Nozzle control method and device for aviation gas turbofan engine

Citations (2)

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Publication number Priority date Publication date Assignee Title
CN109383793A (en) * 2017-08-07 2019-02-26 深圳光启合众科技有限公司 Vertically taking off and landing flyer and its control method
CN111255567A (en) * 2018-11-30 2020-06-09 劳斯莱斯有限公司 Gas turbine engine

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Publication number Priority date Publication date Assignee Title
US8181442B2 (en) * 2008-05-05 2012-05-22 Pratt & Whitney Canada Corp. Gas turbine aircraft engine with power variability
GB201600180D0 (en) * 2016-01-06 2016-02-17 Rolls Royce Plc Gas turbine engine
GB2547674A (en) * 2016-02-25 2017-08-30 Rolls Royce Plc Gas turbine engine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109383793A (en) * 2017-08-07 2019-02-26 深圳光启合众科技有限公司 Vertically taking off and landing flyer and its control method
CN111255567A (en) * 2018-11-30 2020-06-09 劳斯莱斯有限公司 Gas turbine engine

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