CN108194225B - A kind of low thrust high-performance and low-cost postposition fanjet - Google Patents
A kind of low thrust high-performance and low-cost postposition fanjet Download PDFInfo
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- CN108194225B CN108194225B CN201711156085.2A CN201711156085A CN108194225B CN 108194225 B CN108194225 B CN 108194225B CN 201711156085 A CN201711156085 A CN 201711156085A CN 108194225 B CN108194225 B CN 108194225B
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- casing
- fanjet
- bearing
- jet pipe
- central axis
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Classifications
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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
- F02K3/062—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 aft 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
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- 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
- F02C7/22—Fuel supply systems
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of low thrust high-performance and low-cost postposition fanjets, are related to fanjet technical field.The present invention is using conformal channel diffuser and inclined flow air compressor as compression stage, standing vortex burning chamber is as fuel conversion plants, by combustion chamber and high-pressure turbine, and turbine and fan integrated design, structure design is simplified using fuel oil lubricating system, the postposition fanjet scheme for ultimately forming the Ultra Low Cost of low thrust magnitude can be widely used in unmanned plane, in target drone market.
Description
Technical field
The present invention relates to fanjet technical fields, and in particular to a kind of low thrust high-performance and low-cost postposition turbofan hair
Motivation.
Background technique
Fanjet is mainly used for the dynamical system of aircraft, generates the power to advance for aircraft.Fanjet
Mainly it is made of fan, compressor, diffuser, combustion chamber, turbine, shafting etc..Shafting is needed by least two or multiple bearings
It is carried, and needs corresponding lubricating and cooling system (lubricating oil, the composition such as oil pump).
Fanjet generallys use fan in engine charge front end.And conventional turbo engine fan is generally and whirlpool
Wheel is driven using an elongated shaft, and the rotor-support-foundation system that forms of entire fan-axis-turbine rotor balancing is proposed it is very high
Requirement, it is also higher to the requirement on machining accuracy of product accordingly, cause rotor-support-foundation system complicated, processing cost is high.Lubricating system
Due to needing individual lubricating oil and oil pump systems, increases fanjet subsystem complexity, improve the complicated journey of installation
Degree and processing cost.
Summary of the invention
(1) technical problems to be solved
The technical problem to be solved by the present invention is how to simplify fanjet structure, engine part quantity, drop are reduced
The production and assembly cost of low engine.
(2) technical solution
In order to solve the above-mentioned technical problems, the present invention provides a kind of low thrust high-performance and low-cost postposition turbofans to start
Machine, comprising: diagonal impeller 1, compressor casing 2, diffuser casing 3, Middle casing 4, outer culvert casing 5, oil feed line 6, turbine
Fan propeller 7, fan guide vane 8, outer culvert jet pipe 9, intension jet pipe 10, turbine guide vane 11, inner cone 12, axle sleeve 13, rear bearing 14, fire
Flame cylinder 15, fore bearing 16, intension casing 17, fuel nozzle 18, central axis 19, clamp nut 20 and rear compression ring 21；
The diagonal impeller 1 is used as compressor rotor, is mounted on the step of central axis 19 by clamp nut 20, front axle
It holds 16 inner ring to be pressed on central axis 19 by diagonal impeller 1,14 inner ring of rear bearing passes through the step structure in rear compression ring 21
It is pressed on 19 step of central axis, rear compression ring 21 is tightened on central axis 19, turbofan rotor 7 and rear compression ring 21
It connects；Diagonal impeller 1, central axis 19, fore bearing 16, rear bearing 14 form rotation system；
16 outer ring of fore bearing is moved radially by the limitation of axle sleeve 13, by the step and Middle casing 4 in axle sleeve 13
Step limitation axial movement；14 outer ring of rear bearing is moved radially by the limitation of axle sleeve 13, passes through step in axle sleeve 13 and center
Step in axis 19 limits axial movement；
The axial force that rotation system generates is transferred to fore bearing 16, rear bearing by the inner ring of fore bearing 16, rear bearing 14
14 bearing ball, then it is transferred to the outer race of fore bearing 16, rear bearing 14, to be transferred to axle sleeve 13, then transmit again
To diffuser casing 3, it is finally transmitted to Middle casing 4；Diffuser casing 3 and Middle casing 4 connect；
Compressor casing 2 is connected to diffuser casing 3；Outer culvert casing 5 is connected to Middle casing 4；Oil feed line 6 is connected to
Outer culvert casing 5；Outer culvert jet pipe 9 and intension jet pipe 10 are integrally welded by fan guide vane 8, and are fixed on Middle casing 4；Inner cone
12 are linked into an integrated entity with intension jet pipe 10 by turbine guide vane 11 in a welding manner；Burner inner liner 15 is connect with intension casing 17；
The circumferentially multiple outlets of fuel nozzle 18 are butted up against the hole that Middle casing 3 matches, and are connected using welding manner.
Preferably, the rear compression ring 21 is by being screwed on central axis 19.
Preferably, the turbofan rotor 7 couples with rear compression ring 21.
Preferably, the diffuser casing 3 is connected with the mode that Middle casing 4 is connected by screw bolts.
Preferably, the compressor casing 2 is connected by screw to diffuser casing 3.
Preferably, the outer culvert casing 5 is connected by screw to Middle casing 4.
Preferably, the oil feed line 6 is connected to outer culvert casing 5 by nipple.
Preferably, it is fixed on by way of screw attachment after the outer culvert jet pipe 9 and intension jet pipe 10 are integrally welded
Middle casing 4.
Preferably, the burner inner liner 15 is connect by the screw at rear portion with intension casing 17.
Preferably, the fuel nozzle 18 circumferentially 12 outlets.
(3) beneficial effect
The present invention is using conformal channel diffuser and inclined flow air compressor as compression stage, and standing vortex burning chamber is as fuel energy
Conversion equipment, by combustion chamber and high-pressure turbine, and turbine and fan integrated design, structure is simplified using fuel oil lubricating system and is set
Meter, ultimately forms the postposition fanjet scheme of the Ultra Low Cost of low thrust magnitude, can be widely used in unmanned plane, target drone city
In, test is proved, thrust ratio can reach 8 magnitudes, and diameter is less than 275mm, and oil consumption rate is less than 0.816kg/ (kgf.h), effect
Fei Bida 1.0.
Detailed description of the invention
Fig. 1 is engine two-dimensional structure schematic diagram of the invention；
Fig. 2 is engine Flame barrel structure schematic diagram of the invention；
Fig. 3 is engine flow path schematic diagram of the invention.
Specific embodiment
To keep the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to of the invention
Specific embodiment is described in further detail.
The determination of inventive engine General structure scheme carries out construction module based on certain long-life turbogenerator
Change, integration, compact designed work.Overall structure takes 0-2-0 support pattern.Core engine is by diagonal flow type compressor, standing vortex
Toroidal combustion chamber, axial flow turbine component, angular contact ceramic ball bearing and its supporting structure composition.It is outer to contain for single-stage postposition fan
(Aft Fan) structure.
In Subsystem Design, part sum is reduced, attachment and transmission system are simplified, simplifies lubricating system, main as follows:
1. outer letter is single stage fan, fan is wide aspect ratio Transonic Blade Profile, and fan postposition is integrated with turbine rotor
Design, compactness are high；
2. compression stage uses single-stage diagonal impeller+conformal channel diffuser of enclosed, have front face area small, high-efficient, logical
The strong feature of stream ability, Middle casing, diffuser integrated design；
3. combustion system uses standing vortex formula combustion chamber, have the characteristics that compact-sized, energy density is high, axial dimension is small,
And nozzle ring and combustion chamber blending section carry out integrated design；
4. expansion system uses the high blow down ratio axial flow turbine of single-stage；
5. cancelling lubricating system, shafting is using the through-flow cooling/lubricating method of fuel oil from back to front；Landline is as follows:
Space → fore bearing → fuel feeding component after pump between fuel oil → fuel feed pipe → bearing holder (housing, cover) → rear bearing → front and back bearings →
Burner inner liner burning；
Specifically, as shown in Figure 1, a kind of low thrust high-performance and low-cost postposition fanjet packet proposed by the present invention
Include: diagonal impeller 1, compressor casing 2, diffuser casing 3, Middle casing 4, outer culvert casing 5, oil feed line 6, turbofan turn
Sub 7, fan guide vane 8, outer culvert jet pipe 9, intension jet pipe 10, turbine guide vane 11, inner cone 12, axle sleeve 13, rear bearing 14, burner inner liner
15, fore bearing 16, intension casing 17, fuel nozzle 18, central axis 19, clamp nut 20 and rear compression ring 21；
1) rotation system
Diagonal impeller 1 is mounted on the step of central axis 19 as compressor rotor by the compression of derotation nut 20；Front axle
It holds 16 inner ring to be pressed on central axis 19 by the structure of diagonal impeller 1,14 inner ring of rear bearing passes through the platform in rear compression ring 21
Stage structure is pressed on 19 step of central axis, and for rear compression ring 21 by being screwed on central axis 19, turbofan rotor 7 is logical
Screw is crossed to couple with rear compression ring 21 --- rotation system is consequently formed.
2) axial force transmission system
16 outer ring of fore bearing is moved radially by the limitation of axle sleeve 13, by the step and Middle casing 4 in axle sleeve 13
Step limitation axial movement.14 outer ring of rear bearing is moved radially by the limitation of axle sleeve 13, passes through step in axle sleeve 13 and center
Step in axis 19 limits axial movement.
The axial force that rotation system generates as a result, is transferred to bearing ball by the inner ring of fore bearing 16, rear bearing 14, passes
It is handed to outer race, is transferred to axle sleeve 13, is transferred to diffuser casing 3, is transferred to Middle casing 4.Wherein, diffuser casing 3
The mode being connected by screw bolts with Middle casing 4.
3) other coupling structures
Compressor casing 2 is connected by screw to diffuser casing 3；Outer culvert casing 5 is connected by screw to Middle casing
4；Oil feed line 6 is connected to outer culvert casing 5 by nipple；Outer culvert jet pipe 9 and intension jet pipe 10 are welded by fan guide vane 8
Integrally, and by way of screw attachment it is fixed on Middle casing 4；Inner cone 12 and intension jet pipe 10 by turbine guide vane 11 with
The mode of welding links into an integrated entity.Burner inner liner 15 is connect by the screw at rear portion with intension casing 17.Fuel nozzle 18 1 weeks altogether
There are 12 outlets, butts up against the hole that Middle casing 3 matches, and connect using welding manner.
As shown in Fig. 2, burner inner liner 15 is by 22 burner inner liner head-shields, 23 burner inner liner inner ring, 24 burner inner liner guiders, 25 burner inner liners
Inner ring back segment, 26 burner inner liner inner ring leading portions composition.Burner inner liner all parts all connect in a welding manner.At the end of burner inner liner 15
End offers screw hole, which is the connecting interface of burner inner liner 15 and intension casing 17.
Air-flow into engine interior is divided into two strands, one air-flow passes through burner inner liner head-shield 22, burner inner liner inner ring leading portion
Hole in 26 enters inside burner inner liner 15；In addition one after cooling flame cylinder guider 24, is passed through by burner inner liner guider 24
Burner inner liner inner ring back segment 25 enters inside burner inner liner 15；Chemistry occurs for the fuel oil after two strands of air-flows and fuel nozzle 18 are atomized instead
It answers, generates high-temperature fuel gas by the runner between burner inner liner guider 24 and be emitted into the turbine in turbofan rotor 7, and push
Turbine rotation acting.
As shown in figure 3, the runner of engine of the invention is divided into intension and outer two strands of culvert.Main duct air-flow passes through oblique flow leaf
1 is taken turns, enters burner inner liner 15 after diffuser 3, combustion chemistry occurs with fuel oil and reacts；Fuel oil is by oil feed line 6, into rear bearing
14 are cooled down, and by the fuel flow path formed between axle sleeve 13 and axis 19, are then cooled down by fore bearing 16, and laggard
Enter fuel nozzle 18 to be atomized, then enter burner inner liner 15, combustion chemistry occurs with intension air and reacts.It is generated after burning
High-temperature fuel gas does work by turbofan rotor 7, is rectified using turbine guide vane 11, then flows through intension casing 17
The runner formed between inner cone 12 is emitted into 10 tail portion of intension jet pipe.
By-pass air duct air then passes through turbine wind by the air flow channel formed between outer culvert casing 5 and intension casing 17
The blade of fan rotor 7 is pressurized, and is then rectified by fan guide vane 8, then by outer culvert jet pipe 9 and intension jet pipe 10
Between runner, injection and is emitted into atmospheric environment after intension Gas Mixing in Cross flow to 10 tail portion of intension jet pipe.
As can be seen that a kind of low thrust fanjet for high efficiency-cost ratio that the present invention designs.It has a characteristic that
1) the conformal channel diffuser compression scheme of enclosed is used.The technology can significantly reduce compression stage diameter, improve whole
Stage efficiency and total pressure recovery coefficient have significant low loss, high diffusion degree advantage, and Middle casing is integrally set with diffuser
Meter, advantageously reduces production cost and engine weight.
2) standing vortex formula combustion technology is used.The length of flame of standing vortex burning chamber only have conventional combustion room 50% or so, it is poor
The oily more conventional rotational-flow stable-flame mode of blowoff limit expands nearly 4 times, efficiency of combustion has height 99% or more in broad range
Energy density, ultra-compact, wide envelope curve feature.
3) using the cooling rotor-loop fueling technology of fuel oil.After the cooling shafting of fuel oil, it is injected into combustion chamber mist
Change, blending, combustion technology, lubricating system, cooling system can be simplified, significantly reduces engine main screw lift.
4) using fan and turbine rotor integrated technique.By turbine rotor and fan propeller integrated design, pass through whirlpool
The flowing that the comb tooth in fan propeller separates intension and outer culvert is taken turns, shafting structure can be simplified, mitigate shafting total weight, is improved tight
Degree of gathering shortens the total length of core engine, improves the reliability of core engine.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformations can also be made, these improvement and deformations
Also it should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of low thrust high-performance and low-cost postposition fanjet characterized by comprising diagonal impeller (1), compressor
Casing (2), diffuser casing (3), Middle casing (4), outer culvert casing (5), oil feed line (6), turbofan rotor (7), wind
Fan guide vane (8), outer culvert jet pipe (9), intension jet pipe (10), turbine guide vane (11), inner cone (12), axle sleeve (13), rear bearing (14),
Burner inner liner (15), fore bearing (16), intension casing (17), fuel nozzle (18), central axis (19), clamp nut (20) and rear pressure
Tight ring (21)；
The diagonal impeller (1) is used as compressor rotor, is mounted on the step of central axis (19) by clamp nut (20), preceding
Bearing (16) inner ring is pressed on central axis (19) by diagonal impeller (1), and rear bearing (14) inner ring passes through rear compression ring (21)
In step structure be pressed on central axis (19) step, rear compression ring (21) is tightened on central axis (19), turbofan turn
Sub (7) couple with rear compression ring (21)；Diagonal impeller (1), central axis (19), fore bearing (16), rear bearing (14) composition rotation
System；
Fore bearing (16) outer ring is moved radially by axle sleeve (13) limitation, passes through the step and Middle casing in axle sleeve (13)
(4) step in limits axial movement；Rear bearing (14) outer ring is moved radially by axle sleeve (13) limitation, by axle sleeve (13)
Step and central axis (19) in step limit axial movement；
The axial force that the rotation system generates by the inner ring of fore bearing (16), rear bearing (14) be transferred to fore bearing (16),
The bearing ball of rear bearing (14), then it is transferred to the outer race of fore bearing (16), rear bearing (14), to be transferred to axle sleeve
(13), diffuser casing (3) are then secondly transferred to, Middle casing (4) are finally transmitted to；Diffuser casing (3) and Middle casing
(4) it connects；
The compressor casing (2) is connected to diffuser casing (3)；Outer culvert casing (5) is connected to Middle casing (4)；Fuel feed pump
Road (6) is connected to outer culvert casing (5)；Outer culvert jet pipe (9) and intension jet pipe (10) are integrally welded by fan guide vane (8), and
It is fixed on Middle casing (4)；Inner cone (12) and intension jet pipe (10) pass through turbine guide vane (11) and connect into one in a welding manner
Body；Burner inner liner (15) is connect with intension casing (17)；Fuel nozzle (18) circumferentially multiple outlets, butt up against Middle casing
(4) hole to match, and connected using welding manner.
2. fanjet as described in claim 1, which is characterized in that it is described after compression ring (21) by being screwed in
In mandrel (19).
3. fanjet as described in claim 1, which is characterized in that the diffuser casing (3) and Middle casing (4) are adopted
The mode being connected with connects.
4. fanjet as described in claim 1, which is characterized in that the compressor casing (2) be connected by screw to
Diffuser casing (3).
5. fanjet as described in claim 1, which is characterized in that the outer culvert casing (5) is connected by screw into
Jie's casing (4).
6. fanjet as described in claim 1, which is characterized in that the oil feed line (6) is connected by nipple
To outer culvert casing (5).
7. fanjet as described in claim 1, which is characterized in that the outer culvert jet pipe (9) and intension jet pipe (10) weldering
It is connected into after one and is fixed on Middle casing (4) by way of screw attachment.
8. fanjet as described in claim 1, which is characterized in that the burner inner liner (15) by the screw at rear portion with it is interior
Contain casing (17) connection.
9. such as fanjet described in any item of the claim 1 to 8, which is characterized in that the fuel nozzle (18) is circumferential
Arrange 12 outlets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711156085.2A CN108194225B (en) | 2017-11-20 | 2017-11-20 | A kind of low thrust high-performance and low-cost postposition fanjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711156085.2A CN108194225B (en) | 2017-11-20 | 2017-11-20 | A kind of low thrust high-performance and low-cost postposition fanjet |
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| Publication Number | Publication Date |
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| CN108194225A CN108194225A (en) | 2018-06-22 |
| CN108194225B true CN108194225B (en) | 2019-06-07 |
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| CN201711156085.2A Active CN108194225B (en) | 2017-11-20 | 2017-11-20 | A kind of low thrust high-performance and low-cost postposition fanjet |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109268168A (en) * | 2018-11-26 | 2019-01-25 | 北京金朋达航空科技有限公司 | Height pushes away the small-size turbojet engine of ratio |
| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113982780B (en) * | 2021-09-27 | 2023-04-07 | 太仓点石航空动力有限公司 | Ring-packaged double-duct variable cycle engine and control method |
| CN114484505B (en) * | 2022-01-27 | 2023-05-16 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite full-ring flame tube, shaping mold and preparation method thereof |
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| CN101149026A (en) * | 2007-11-08 | 2008-03-26 | 北京航空航天大学 | Turbine fan engine and design method thereof |
| CN201739027U (en) * | 2010-06-22 | 2011-02-09 | 季承 | Turbofan rear-mounted engine |
| CN105705748A (en) * | 2013-09-03 | 2016-06-22 | 以色列宇航工业有限公司 | Engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2950381B1 (en) * | 2009-09-18 | 2011-10-28 | Snecma | TURBOMACHINE WITH NON-CARINE CONTRAROTATIVE PROPELLERS |
| EP2535519A3 (en) * | 2011-06-14 | 2014-11-12 | Rolls-Royce plc | A retention device for a rotating blade |
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- 2017-11-20 CN CN201711156085.2A patent/CN108194225B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101149026A (en) * | 2007-11-08 | 2008-03-26 | 北京航空航天大学 | Turbine fan engine and design method thereof |
| CN201739027U (en) * | 2010-06-22 | 2011-02-09 | 季承 | Turbofan rear-mounted engine |
| CN105705748A (en) * | 2013-09-03 | 2016-06-22 | 以色列宇航工业有限公司 | Engine |
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| CN108194225A (en) | 2018-06-22 |
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