CN113738532A - Aero-engine with overlapped ducts - Google Patents
Aero-engine with overlapped ducts Download PDFInfo
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- CN113738532A CN113738532A CN202111300881.5A CN202111300881A CN113738532A CN 113738532 A CN113738532 A CN 113738532A CN 202111300881 A CN202111300881 A CN 202111300881A CN 113738532 A CN113738532 A CN 113738532A
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- rotor
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- supercharging
- culvert
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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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
- F04D19/00—Axial-flow pumps
- F04D19/002—Axial flow fans
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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
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
Abstract
The application relates to the field of aircraft engines, in particular to an overlapped ducted aircraft engine.A supercharging rotor part is arranged between an axial flow fan and a core machine, and the radial height of the rotor of the supercharging rotor part is set to be the same as that of the rotor of the axial flow fan and the rotating speed of the rotor of the axial flow fan, so that the larger supercharging ratio and total pressure ratio of the aircraft engine are improved by a smaller number of stages; connect high temperature culvert passageway with axial fan's export outer loop, connect low temperature culvert passageway with axial fan's export inner loop, exhaust in to high temperature culvert passageway and low temperature culvert passageway is shunted through setting up the splitter ring quick-witted casket, high temperature culvert passageway can have certain crisscross with low temperature culvert passageway after pressure boost rotor spare, carry out the heat exchange at crisscross position through the exhaust with in two passageways, culvert carminative temperature in the high temperature can be effectively reduced, satisfy the temperature demand of core machine entry, make aeroengine can be at the stable work of suitable temperature interval.
Description
Technical Field
The application belongs to the field of aircraft engines, and particularly relates to an overlapping duct aircraft engine.
Background
In a conventional double-rotor turbofan engine, in order to achieve the goal of high total pressure ratio, technical means such as increasing the number of rotor stages and increasing the rotation speed of the rotor are often adopted. The technical background provided by the invention is to analyze how to develop a middle-duct turbofan engine with high total pressure ratio, mixed exhaust and relatively limited outline size based on a mature core machine with a high-pressure compressor with relatively low pressure ratio and a single-stage high-pressure turbine with relatively limited temperature resistance; the pressure ratio of a high-pressure compressor of a mature core machine is limited, the temperature limiting requirements are respectively arranged at the outlet of the high-pressure compressor and the inlet of a high-pressure turbine, and the external pressure ratio in the low-pressure compressor is not allowed to be too high in the overall matching mode of mixed exhaust, so that a technical method needs to be created to realize higher internal pressure ratio of the low-pressure compressor, realize higher total pressure ratio of an aircraft engine overall, control the weight control, size limitation, configuration complexity and the like, and how to realize the requirements of double pressure ratio, temperature and external pressure ratio under the condition of not increasing too many rotor series or adopting complex configurations such as gear transmission/three rotors and the like.
Some of the related prior art disadvantages:
1. in the conventional dual-rotor aero-engine structure, the rotating speed of a booster-stage rotor is the same as that of an axial-flow fan rotor, but the radial height of the tip of the booster-stage rotor is far lower than that of the axial-flow fan rotor, so that the linear speed of the tip of the booster-stage rotor is far lower than that of the tip of the axial-flow fan rotor, the stage pressure of blades of the booster-stage rotor is lower, and a larger booster ratio is difficult to form by adopting fewer stages;
2. in the existing scheme, after the high supercharging ratio is barely realized by increasing the number of stages, the problems of weight, cost, engine length and the like are increased due to excessive number of stages;
3. in the existing scheme, when the target of high total pressure ratio is realized, the temperature of airflow entering the mature core machine is too high due to higher pressure ratio of the axial flow fan and the pressure increasing stage, the requirement of limiting temperature of an outlet of a high-pressure air compressor can be rapidly exceeded, a cooling air source with relatively low temperature cannot be provided for a high-pressure turbine, the existing mature core machine cannot be fully utilized, and the application potential of the mature core machine cannot be further expanded.
Therefore, the problem how to reduce the number of stages and reduce the temperature simultaneously while ensuring a higher pressurization ratio is a problem to be solved.
Disclosure of Invention
The utility model provides an overlap duct aeroengine is provided to solve prior art and be difficult to when guaranteeing higher pressure-increasing ratio, the more, the great problem of intension temperature of progression.
The technical scheme of the application is as follows: an overlapping ducted aircraft engine comprises a low-pressure shafting, a core machine and a bearing casing, wherein the low-pressure shafting comprises a multistage low-pressure turbine arranged at the rear end, a multistage low-pressure turbine shaft which is coaxial with the center line of the aircraft engine and penetrates through the core machine, and an axial flow fan arranged at the front end, the multistage low-pressure turbine works to drive the multistage low-pressure turbine shaft and the axial flow fan to rotate, a splitter ring casing and a supercharging rotor part which are coaxially arranged with the multistage low-pressure turbine shaft are arranged between the axial flow fan and the core machine, the splitter ring casing is a stator part and is connected with the bearing casing, and the supercharging rotor part is connected with the axial flow fan and is driven by the axial flow fan rotor to rotate; the supercharging rotor piece is a two-stage rotor piece, and the radial height of the rotor of the supercharging rotor piece is the same as that of the rotor of the axial flow fan and the rotating speed of the supercharging rotor piece is the same; the outer ring of an outlet of the axial flow fan is connected with a high-temperature culvert channel, the inner ring of the outlet of the axial flow fan is connected with a low-temperature culvert channel, the high-temperature culvert channel and the low-temperature culvert channel are shunted through a shunt ring casing, the high-temperature culvert channel is connected between a shunt circulation outlet and an inlet of a pressurizing rotor piece along the outside of the aircraft engine, and then enters the interior of the aircraft engine from an outlet of the pressurizing rotor piece to be connected with a core machine; the low temperature culvert passageway sets up along aeroengine is inside, when the high temperature culvert passageway between pressure boost rotor spare and the core machine, the low temperature culvert passageway is crisscross with the high temperature culvert passageway and both inside airflows carry out the heat exchange, then the low temperature culvert passageway sets up along aeroengine's outside.
Preferably, the supercharging rotor member is connected to the axial fan and is rotated by the axial fan rotor.
Preferably, the axial flow fan comprises a primary axial flow fan rotor and a secondary axial flow fan rotor, and a first full-ring blade shroud is arranged at the outer edge of the secondary axial flow fan rotor; the supercharging rotor part comprises a supercharging stage one-level rotor and a supercharging stage two-level rotor, the supercharging stage one-level rotor and the supercharging stage two-level rotor are both arranged on the splitter ring casing, a second whole-ring blade cap is arranged at the outer edge of the supercharging stage one-level rotor, a third whole-ring blade cap is arranged at the outer edge of the supercharging stage two-level rotor, the first whole-ring blade cap is connected with the second whole-ring blade cap, and the second whole-ring blade cap is connected with the third whole-ring blade cap.
Preferably, the first whole-ring blade crown and the second whole-ring blade crown are respectively provided with a first flange edge which is adjacently arranged, and a first connecting piece for fixing the first flange edges of the first whole-ring blade crown and the second whole-ring blade crown is arranged between the first whole-ring blade crown and the second whole-ring blade crown; and second flange edges which are adjacently arranged are arranged on the second whole-ring blade crown and the third whole-ring blade crown, and a second connecting piece for fixing the second flange edges between the second whole-ring blade crown and the third whole-ring blade crown is arranged between the second whole-ring blade crown and the third whole-ring blade crown.
Preferably, the inner ring of the booster stage primary rotor is connected with a first disk body, and the inner ring of the booster stage secondary rotor is connected with a second disk body.
Preferably, the axial-flow fan comprises an air inlet casing, a fan short shaft is arranged between the axial-flow fan and the multistage low-pressure turbine shaft and is coaxially arranged with the multistage low-pressure turbine shaft, the fan short shaft comprises a connecting section, a transition section and a supporting section, the connecting section, the transition section and the supporting section are located at two ends of the fan short shaft, the connecting section is respectively connected with the air inlet casing and the multistage low-pressure turbine shaft, the transition section is arranged between the connecting section and the supporting section, the diameter of the transition section is gradually increased from the connecting section to the supporting section, and a primary rotor of the axial-flow fan and a secondary rotor of the axial-flow fan are arranged on the supporting section.
Preferably, the axial fan secondary rotor, the booster stage primary rotor and the booster stage secondary rotor are all of a blisk/ring structure.
Preferably, the bearing case comprises an intermediary case, the intermediary case is arranged between the pressurizing rotor part and the core machine, an inner duct overlapping area (10) and an outer duct overlapping area (10) which are annularly arranged are arranged in the intermediary case, the inner duct overlapping area and the outer duct overlapping area (10) are provided with high-temperature heat exchange channels and low-temperature heat exchange channels which are alternately distributed at intervals, the high-temperature heat exchange channels are communicated with high-temperature inner duct channels, the low-temperature heat exchange channels are communicated with low-temperature outer duct channels, and partition plates made of heat conduction materials are arranged between the low-temperature heat exchange channels and the high-temperature heat exchange channels.
Preferably, the high-temperature culvert channel between the pressurizing rotor piece and the inner and outer culvert overlapping area (10) is a whole annular channel, then the high-temperature culvert channel is divided into a plurality of channels which are annularly arranged and are arranged at intervals and connected with the high-temperature heat exchange channel, and the high-temperature culvert channel is led out from the high-temperature heat exchange channel and then forms the whole annular channel again to be connected with the inlet of the core machine.
Preferably, a second ball bearing is connected between the supercharging rotor piece and the multi-stage low-pressure turbine shaft, and a first ball bearing is connected between the intermediate casing and the core machine.
According to the overlapping ducted aircraft engine, the pressurizing rotor piece is arranged between the axial flow fan and the core machine, the radial height of the rotor of the pressurizing rotor piece is set to be the same as that of the rotor of the axial flow fan, and the rotating speed of the pressurizing rotor piece is the same, so that the larger pressurizing ratio and total pressure ratio of the aircraft engine are improved by a smaller number of stages; connect high temperature culvert passageway with axial fan's export outer loop, connect low temperature culvert passageway with axial fan's export inner loop, exhaust in to high temperature culvert passageway and low temperature culvert passageway is shunted through setting up the splitter ring quick-witted casket, high temperature culvert passageway can have certain crisscross with low temperature culvert passageway after pressure boost rotor spare, carry out the heat exchange at crisscross position through the exhaust with in two passageways, culvert carminative temperature in the high temperature can be effectively reduced, satisfy the temperature demand of core machine entry, make aeroengine can be at the stable work of suitable temperature interval.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of the overall structure of the present application;
FIG. 2 is a schematic view of a low pressure rotor of the present application;
FIG. 3 is a schematic view of the bypass flow direction structure of the present application;
FIG. 4 is a schematic view of the bypass flow direction structure of the present application;
FIG. 5 is a schematic view of the inner and outer overlapping areas of the intermediate casing of the present application.
1. An air inlet; 2. an air inlet casing; 3. an axial flow fan; 4. a primary guide blade of the axial flow fan; 5. a diverter ring casing; 6. a high temperature culvert channel; 7. a low-temperature culvert channel; 8. a booster stage first stage guide vane; 9. a booster stage secondary guide vane; 10. an inner and outer duct overlap region; 11. an intermediary case; 12. an outer duct air inlet; 13. a high pressure air inlet; 14. a high pressure compressor; 15. a combustion chamber; 16. a high pressure turbine; 17. an inter-turbine casing; 18. a multi-stage low pressure turbine; 19. an exhaust port; 20. a first roller bearing; 21. a second roller bearing; 22. a low-pressure turbine shaft; 23. a first ball bearing; 24. a second ball bearing; 25. a third roller bearing; 26. a primary rotor of an axial fan; 27. a secondary rotor of an axial fan; 28. a first whole ring tip shroud; 29. a first flanged edge; 30. a first connecting member; 31. a second whole ring tip shroud; 32. a booster stage first-stage rotor; 33. a first tray body; 34. a second flanged edge; 35. a second connecting member; 36. a third whole-ring tip shroud; 37. a booster stage secondary rotor; 38. a second tray body; 39. an entage airflow direction indicating line; 40. and an outer culvert airflow direction indicating line.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An aircraft engine with overlapped ducts is shown in figures 1-4 and comprises a low-pressure shafting, a core machine and a bearing casing. The low-pressure shafting passes through the core machine and is located the both sides of core machine, and the low-pressure shafting includes axial fan 3, low-pressure turbine shaft 22 and multistage low-pressure turbine 18, and multistage low-pressure turbine 18 is located the rear portion of core machine, and low-pressure turbine shaft 22 passes through the high-pressure shafting with the coaxial setting of aeroengine's central line, and low-pressure turbine shaft 22 provides power and drives low-pressure turbine shaft 22 and axial fan 3 and rotate, and axial fan 3 work discharges inner duct air current and outer duct air current, and inner duct air current enters into the core machine and supplies the core machine work, and outer duct air current is discharged from the core machine outboard.
The core machine comprises a high-pressure compressor 14, an annular combustion chamber 15 and a high-pressure turbine 16, wherein the high-pressure turbine 16 drives the high-pressure compressor 14 to work and provides high temperature and high pressure to drive the annular combustion chamber 15 to burn so as to realize power output.
Wherein, the inlet of the aircraft engine is the front end thereof, and the outlet is the rear end thereof.
A splitter ring casing 5 and a supercharging rotor part which are coaxially arranged with the low-pressure turbine shaft 22 are arranged between the axial flow fan 3 and the core machine, and the splitter ring casing 5 is a stator part and is connected with a bearing casing; the supercharging rotor piece is a two-stage rotor piece, the radial height of the rotor of the supercharging rotor piece is the same as or similar to that of the rotor of the axial flow fan 3, and the rotating speeds of the supercharging rotor piece and the rotor of the axial flow fan are the same;
the axial flow fan 3 is connected with an air inlet 1 of an aeroengine, an outer ring of an outlet of a rotor of the axial flow fan 3 is connected with a high-temperature content channel 6, an inner ring of an outlet of a rotor of the axial flow fan 3 is connected with a low-temperature content channel 7, the high-temperature content channel 6 is positioned on the outer side of the low-temperature content channel 7, the high-temperature content channel 6 and the low-temperature content channel are shunted through a shunting ring casing 5, the high-temperature content channel 6 is connected between an outlet of the shunting ring casing 5 and an inlet of a pressurizing rotor piece along the outside of the aeroengine, and then enters a high-pressure air inlet 13 at the front end of a high-pressure compressor 14 from an outlet of the pressurizing rotor piece to be connected with a core machine, and the whole flow direction of content air flow advances along a content air flow direction indicating line 39 in the graph 3; low temperature culvert passageway 7 is along the inside setting of aeroengine, when high temperature culvert passageway 6 between pressure boost rotor spare and the core machine, low temperature culvert passageway 7 and high temperature culvert passageway 6 are crisscross and both inside airflows carry out the heat exchange, then low temperature culvert passageway 7 enters into the outer culvert way air inlet 12 department that the core machine dug the side, then set up and extend to 19 departments of gas vent along the outside of core machine, mix the discharge with the culvert way air current when 19 departments of gas vent, the whole flow direction of culvert air current advances along the culvert air current flow direction indicating line 40 in figure 4.
The radial height of the rotor of the supercharging rotor part is the same as that of the rotor of the axial flow fan 3, the rotating speed is the same, the supercharging rotor part can generate higher supercharging ratio when working, and only a double-rotor aero-engine structure with fewer stages is adopted, the aim of high total pressure ratio can be achieved, for the problem of temperature increase caused by high supercharging ratio, the high-temperature bypass channel 6 is connected with the outlet outer ring of the rotor of the axial flow fan 3, the low-temperature outer ring channel is connected with the outlet inner ring of the rotor of the axial flow fan 3, so that the outer bypass airflow in the low-temperature bypass channel 7 and the inner bypass airflow in the high-temperature bypass channel 6 can be crossed to certain extent when being discharged, heat exchange is carried out at the crossed position to cool the inner bypass airflow, the cooled inner bypass airflow meets the working requirement of the core engine, and the number of stages of the aero-engine is small, therefore, the engine is light in weight, low in cost, short in length and reasonable in overall spatial structure arrangement.
Preferably, the supercharging rotor piece is connected with the axial flow fan 3 and is driven by the rotor of the axial flow fan 3 to rotate, so that the supercharging rotor piece and the low-pressure turbine shaft 22 have enough space while the supercharging rotor piece can work normally, the low-temperature bypass channel 7 can have enough space to bypass the supercharging rotor piece for exhausting, and the space arrangement is reasonable.
Preferably, the axial flow fan 3 comprises a fan primary rotor 26, a fan secondary rotor 27, and a fan primary guide blade 4, wherein the fan primary guide blade 4 is arranged between the fan primary rotor 26 and the fan secondary rotor 27, and a first full-ring blade shroud 28 is arranged at the outer edge of the fan secondary rotor 27; the supercharging rotor part comprises a supercharging stage one-level rotor 32, a supercharging stage one-level guide blade 8, a supercharging stage two-level rotor 37 and a supercharging stage two-level guide blade 9, the supercharging stage one-level rotor 32, the supercharging stage one-level guide blade 8, the supercharging stage two-level rotor 37 and the supercharging stage two-level guide blade 9 are all arranged on the shunting ring casing 5, a second whole ring blade crown 31 is arranged at the outer edge of the supercharging stage one-level rotor 32, a third whole ring blade crown 36 is arranged at the outer edge of the supercharging stage two-level rotor 37, the first whole ring blade crown 28 is connected with the second whole ring blade crown 31, and the second whole ring blade crown 31 is connected with the third whole ring blade crown 36.
The synchronous rotation of the fan primary rotor 26, the fan secondary rotor 27, the booster stage primary rotor 32 and the booster stage secondary rotor 37 is realized by arranging the first integral ring blade shroud 28, the second integral ring blade shroud 31 and the third integral ring blade shroud 36, the structure is stable, and the spatial layout of rotating parts of the booster stage rotor is not influenced by arranging the booster stage primary guide blades 8 and the booster stage secondary guide blades 9 on the splitter box 5.
Preferably, the first whole-ring blade shroud 28 and the second whole-ring blade shroud 31 are both provided with first flange edges 29 which are adjacently arranged, and a first connecting piece 30 for fixing the first flange edges 29 of the first whole-ring blade shroud 28 and the second whole-ring blade shroud 31 is arranged between the first whole-ring blade shroud 28 and the second whole-ring blade shroud 31; the second integral ring blade crown 31 and the third integral ring blade crown 36 are respectively provided with a second flange edge 34 which is adjacently arranged, and a second connecting piece 35 which is used for fixing the second flange edges 34 of the second integral ring blade crown 31 and the third integral ring blade crown 36 is arranged between the second integral ring blade crown 31 and the third integral ring blade crown 36. The connecting pieces can be bolts and the like, the fan secondary rotor 27 and the pressure increasing stage primary rotor 32 and the pressure increasing stage secondary rotor 37 can be tightly and stably fixed through arrangement of the connecting pieces, and rotation synchronization among the fan secondary rotor 27, the pressure increasing stage primary rotor 32 and the pressure increasing stage secondary rotor 37 is effectively guaranteed.
Preferably, a first disk 33 is attached to the inner ring of the booster stage primary rotor 32 and a second disk 38 is attached to the inner ring of the booster stage secondary rotor 37. The first disk body 33 and the second disk body 38 can respectively and stably support the pressure increasing stage one-level rotor 32 and the pressure increasing stage two-level rotor 37, so that the pressure increasing stage one-level rotor 32 and the pressure increasing stage two-level rotor 37 are prevented from being deformed in the working process, and the working stability of the pressure increasing stage rotor is ensured.
Preferably, the fan short shaft structure further comprises an air inlet casing 2, a fan short shaft is arranged between the axial flow fan 3 and the low-pressure turbine shaft 22 and is coaxially arranged with the low-pressure turbine shaft 22, the fan short shaft comprises a connecting section, a transition section and a supporting section which are arranged at two ends, the two connecting sections are respectively connected with the air inlet casing 2 and the low-pressure turbine shaft 22, the transition section is arranged between the connecting section and the supporting section, the diameter of the transition section is gradually increased from the connecting section to the supporting section, and a fan primary rotor 26 and a fan secondary rotor 27 are arranged on the supporting section. Through setting up the great support section of diameter, can guarantee that axial-flow fan 3 and pressure boost rotor spare all have good pressure boost ratio.
Preferably, the fan secondary rotor 27, the booster stage primary rotor 32 and the booster stage secondary rotor 37 are all of an integral bladed disc/ring structure, so as to ensure the rigidity of the fan secondary rotor 27, the booster stage primary rotor 32 and the booster stage secondary rotor 37 and ensure the working stability of the three.
As shown in fig. 5, preferably, the force-bearing casing includes an intermediate casing 11 and an inter-turbine casing 17, the inter-turbine casing 17 is disposed between the high-pressure turbine 16 and the multi-stage low-pressure turbine 18, a second roller bearing 21 is disposed between the high-pressure turbine 16 and the inter-turbine casing 17, a first roller bearing 20 is disposed between the multi-stage low-pressure turbine 18 and the inter-turbine casing 17, the intermediate casing 11 is disposed between the boost rotor member and the core, an inner and outer duct overlapping area 10 is disposed in the intermediate casing 11, the inner and outer duct overlapping area 10 is provided with high-temperature heat exchange channels and low-temperature heat exchange channels which are alternately arranged at intervals, the high-temperature heat exchange channels are communicated with the high-temperature inner duct channel 6, the low-temperature heat exchange channels are communicated with the low-temperature outer duct channel 7, and a partition plate made of a heat conductive material is disposed between the low-temperature heat exchange channels and the high-temperature heat exchange channels.
Through setting up inside and outside duct overlap area 10 of crisscross arrangement, thereby can guarantee outside duct air current and inside duct air current and have enough big heat transfer area and carry out effectual heat transfer, the setting up of baffle has guaranteed the closure between low temperature heat transfer passageway and the high temperature heat transfer passageway.
Preferably, the high-temperature culvert channel 6 between the pressurizing rotor piece and the inner and outer culvert overlapping area 10 is a whole annular channel, then is divided into a plurality of channels which are annularly arranged and arranged at intervals and is connected with the high-temperature heat exchange channel, and is led out from the high-temperature heat exchange channel to form the whole annular channel again and is connected with the inlet of the core machine. The high-temperature culvert channels 6 at the inlet and the outlet of the inner and outer culvert overlapping area 10 are all set to be whole annular channels, so that the high efficiency and smoothness of the inner culvert airflow when entering the inner and outer culvert overlapping area 10 and the core machine are ensured. The low-temperature bypass channel 7 at the inlet and the outlet of the inner and outer bypass overlapping area 10 is also in a whole ring shape, so that the smoothness of the air flow of the outer bypass is ensured.
Preferably, a second ball bearing 24 is connected between the supercharging rotor member and the low-pressure turbine shaft 22, a first ball bearing 23 is connected between the intermediate casing 11 and the core, and a third roller bearing 25 is arranged between the air inlet casing 2 and the fan stub shaft. The intermediate casing 11 and the inter-turbine casing 17 stably support the core machine through the first ball bearing 23 and the second roller bearing 21, and stably support the low-pressure shafting and the supercharging rotor through the first roller bearing 20, the second ball bearing 24 and the third roller bearing 25.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an overlap duct aeroengine, includes low pressure shafting, core machine and load-bearing machine casket, low pressure shafting is including multistage low-pressure turbine (18) of locating the rear end, coaxial and pass low-pressure turbine shaft (22) that the core machine set up with aeroengine's central line, locate axial fan (3) of front end, multistage low-pressure turbine (18) work drives low-pressure turbine shaft (22) and axial fan (3) and rotates its characterized in that:
a splitter ring casing (5) and a supercharging rotor piece which are coaxially arranged with the low-pressure turbine shaft (22) are arranged between the axial flow fan (3) and the core machine, and the splitter ring casing (5) is a stator piece and is connected with the bearing casing; the supercharging rotor piece is a two-stage rotor piece, the radial height of the rotor of the supercharging rotor piece is the same as that of the rotor of the axial flow fan (3), and the rotating speed of the supercharging rotor piece is the same;
the outer ring of an outlet of the axial flow fan (3) is connected with a high-temperature culvert channel (6), the inner ring of the outlet of the axial flow fan (3) is connected with a low-temperature culvert channel (7), the high-temperature culvert channel (6) and the low-temperature culvert channel are shunted through a shunting ring casing (5), the high-temperature culvert channel (6) is connected between an outlet of the shunting casing (5) and an inlet of a pressurizing rotor piece along the outside of the aircraft engine, and then enters the interior of the aircraft engine from an outlet of the pressurizing rotor piece to be connected with a core machine; low temperature culvert passageway (7) is along aeroengine inside setting, when high temperature culvert passageway (6) between pressure boost rotor spare and the core machine, low temperature culvert passageway (7) and high temperature culvert passageway (6) are crisscross and both inside airflows carry out the heat exchange, and then low temperature culvert passageway (7) set up along aeroengine's outside.
2. The overlapping ducted aircraft engine of claim 1, wherein: the supercharging rotor part is connected with the axial flow fan (3) and is driven by the rotor of the axial flow fan (3) to rotate.
3. The overlapping ducted aircraft engine of claim 2, wherein: the axial flow fan (3) comprises a fan primary rotor (26) and a fan secondary rotor (27), and a first whole-ring blade shroud (28) is arranged at the outer edge of the fan secondary rotor (27); the supercharging rotor part comprises a supercharging stage one-level rotor (32), a supercharging stage one-level guide blade (8), a supercharging stage two-level rotor (37) and a supercharging stage two-level guide blade (9), wherein the supercharging stage one-level rotor (32), the supercharging stage one-level guide blade (8), the supercharging stage two-level rotor (37) and the supercharging stage two-level guide blade (9) are all arranged on the shunting ring casing (5), a second whole ring blade shroud (31) is arranged at the outer edge of the supercharging stage one-level rotor (32), a third whole ring blade shroud (36) is arranged at the outer edge of the supercharging stage two-level rotor (37), the first whole ring blade shroud (28) is connected with the second whole ring blade shroud (31), and the second whole ring blade shroud (31) is connected with the third whole ring blade shroud (36).
4. The overlapping ducted aircraft engine of claim 3, wherein: the first whole-ring blade crown (28) and the second whole-ring blade crown (31) are respectively provided with a first flange edge (29) which are adjacently arranged, and a first connecting piece (30) for fixing the first flange edges (29) of the first whole-ring blade crown (28) and the second whole-ring blade crown (31) is arranged between the first whole-ring blade crown and the second whole-ring blade crown (31); and second flange edges (34) which are adjacently arranged are respectively arranged on the second integral-ring blade crown (31) and the third integral-ring blade crown (36), and a second connecting piece (35) for fixing the second flange edges (34) between the second integral-ring blade crown (31) and the third integral-ring blade crown (36) is arranged between the second integral-ring blade crown and the third integral-ring blade crown.
5. The overlapping ducted aircraft engine of claim 3, wherein: the inner ring of the booster stage primary rotor (32) is connected with a first disc body (33), and the inner ring of the booster stage secondary rotor (37) is connected with a second disc body (38).
6. The overlapping ducted aircraft engine of claim 3, wherein: still include air inlet machine casket (2), be provided with the fan minor axis between axial fan (3) and low-pressure turbine shaft (22), fan minor axis and low-pressure turbine shaft (22) coaxial setting, the fan minor axis is including linkage segment, changeover portion and the support section that is located both ends, two sections the linkage segment links to each other with air inlet machine casket (2) and low-pressure turbine shaft (22) respectively, the changeover portion is located between linkage segment and the support section and its diameter is crescent from linkage segment to support section, fan one-level rotor (26) and fan second grade rotor (27) are located on the support section.
7. The overlapping ducted aircraft engine of claim 3, wherein: the fan secondary rotor (27), the booster stage primary rotor (32) and the booster stage secondary rotor (37) are all of a blisk/ring structure.
8. The overlapping ducted aircraft engine of claim 1, wherein: the bearing case comprises an intermediate case (11), the intermediate case (11) is arranged between a pressurizing rotor part and a core machine, an inner duct and outer duct overlapping area (10) which is annularly arranged is arranged in the intermediate case (11), the inner duct and outer duct overlapping area (10) is provided with high-temperature heat exchange channels and low-temperature heat exchange channels which are arranged at intervals in a staggered mode, the high-temperature heat exchange channels are communicated with high-temperature inner duct channels (6), the low-temperature heat exchange channels are communicated with low-temperature outer duct channels (7), and a partition plate made of a heat conduction material is arranged between the low-temperature heat exchange channels and the high-temperature heat exchange channels.
9. The overlapping ducted aircraft engine of claim 8, wherein: the high-temperature inner culvert channel (6) between the supercharging rotor piece and the inner culvert and outer culvert overlapping area (10) is a whole annular channel, then the high-temperature inner culvert channel is divided into a plurality of channels which are annularly arranged and are arranged at intervals and connected with the high-temperature heat exchange channel, and the whole annular channel is formed again after the high-temperature heat exchange channel is led out and connected with the inlet of the core machine.
10. The overlapping ducted aircraft engine of claim 8, wherein: a second ball bearing (24) is connected between the supercharging rotor piece and the low-pressure turbine shaft (22), and a first ball bearing (23) is connected between the intermediate casing (11) and the core machine.
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