CN109854377A - A kind of novel aerial turbo fan engine - Google Patents
A kind of novel aerial turbo fan engine Download PDFInfo
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- CN109854377A CN109854377A CN201910274675.8A CN201910274675A CN109854377A CN 109854377 A CN109854377 A CN 109854377A CN 201910274675 A CN201910274675 A CN 201910274675A CN 109854377 A CN109854377 A CN 109854377A
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 6
- 230000004323 axial length Effects 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Abstract
The present invention relates to a kind of aircraft power plants, and in particular to a kind of novel aerial turbo fan engine.Technical solution is as follows: including first order fan, second level fan, compressor, combustion chamber, high-pressure turbine, low-pressure turbine, the first retarder and the second retarder, first order fan, the first retarder and low-pressure turbine form low pressure rotor system, first order fan one end is mounted in first bearing and the other end is connected with the first retarder, and the other end of the first retarder is connected by low-pressure turbine shaft with low-pressure turbine；Second level fan, the second retarder, compressor and high-pressure turbine form high pressure rotor system, and second level fan is connected with one end of the second retarder, and the other end of the second retarder is connected with the preceding axle journal of compressor.The present invention has many advantages, such as that gyroscopic couple is small, compact-sized, light-weight, high-efficient.
Description
Technical field
The present invention relates to a kind of aircraft power plants, and in particular to a kind of novel aerial turbo fan engine.
Background technique
Turbofan is a kind of important structure type in aero-engine, because its propulsive efficiency is high, thrust is big
And it is used widely.Conventional turbofan engine mainly by fan, compressor, combustion chamber, high-pressure turbine, low-pressure turbine,
The cell cubes such as outer culvert casing, jet pipe composition.Its basic functional principle is the rotation of engine high and low pressure system, by the air of import
Sucking engine interior, portion of air generates a part of thrust through by-pass air duct discharge, another part air compresses through compressor,
Discharge generates another part thrust at a high speed after combustion chambers burn, high-pressure turbine acting.Conventional turbofan engine generallys use
High-pressure turbine drives compressor, low-pressure turbine driving fan, the design philosophy of high and low pressure rotor-support-foundation system rotating Vortex, this work
The advantages of operation mode, is that working principle is clear, the design of pneumatic and structure is simple, but thus bring the disadvantage is that engine rotor system
The gyroscopic couple of system is larger, and stator transition is required between rotors at different levels, and engine axial length is long, main screw lift is big.
Summary of the invention
The present invention provides a kind of novel aerial turbo fan engine, small, compact-sized, light-weight with gyroscopic couple,
The advantages that high-efficient.
Technical scheme is as follows:
A kind of novel aerial turbo fan engine, including first order fan, second level fan, compressor, combustion chamber, height
Turbine, low-pressure turbine, the first retarder and the second retarder are pressed, first order fan, the first retarder and low-pressure turbine composition are low
Rotor-support-foundation system is pressed, the low pressure rotor system is supported in first bearing, 3rd bearing, fourth bearing and 7th bearing, and first
Grade fan one end is mounted in first bearing and the other end is connected with the first retarder, and first bearing is mounted on front housing, the
The other end of one speed reducer is connected by low-pressure turbine shaft with low-pressure turbine, and low-pressure turbine is supported in 7th bearing, the 7th axis
It holds and is mounted on rear housing；3rd bearing and fourth bearing are intershaft bearing, and 3rd bearing is mounted on the first retarder and second
Between grade fan, fourth bearing is mounted between the preceding axle journal of compressor and low-pressure turbine shaft；Second level fan, second are slowed down
Device, compressor and high-pressure turbine form high pressure rotor system, and high pressure rotor system is supported on second bearing, 5th bearing and the 6th
On bearing, second level fan is connected with one end of the second retarder, the preceding axle journal phase of the other end and compressor of the second retarder
Even, high-pressure turbine is supported in 6th bearing, and second bearing and 5th bearing are mounted on Middle casing；6th bearing is intermediary
Bearing is mounted in the rear shaft neck and low-pressure turbine shaft of high-pressure turbine.
Further, the novel aerial turbo fan engine, wherein front housing, Middle casing, compressor casing,
Combustion chamber, outer culvert casing, low-pressure turbine casing, rear housing and jet pipe form the stator system of engine, wherein front housing, intermediary
Casing and rear housing are main support case.
The invention has the benefit that one, novel aerial turbo fan engine of the invention uses high and low pressure rotor system
It unites to the design philosophy turned, reduces the problem of increasing in engine operation because of aspect variation bring gyroscopic couple, together
When the stator blade of subseries is eliminated in high and low pressure rotor-support-foundation system, shorten the length of engine, alleviate complete machine
Weight；Two, novel aerial turbo fan engine of the invention is by designing retarder in high and low pressure rotor-support-foundation system, sufficiently
The ability to work for having played compressor, low-pressure turbine and two-stage fan not only solves the high revolving speed of compressor, low-pressure turbine and wind
The difficult problem of slow-speed of revolution matching is fanned, while improving the efficiency and thrust of engine；Three, its is aero-engine of the invention right
The thought designed that turns and slow down applies also for the technical field that space flight, navigation, automobile etc. have similar requirement.
Detailed description of the invention
Fig. 1 is novel aerial turbo fan engine general structure schematic diagram；
Fig. 2 is high pressure rotor system schematic；
Fig. 3 is low pressure rotor system schematic；
Fig. 4 is engine stator system schematic.
Specific embodiment
As shown in Figure 1, a kind of novel aerial turbo fan engine, including first order fan 2, second level fan 3, calm the anger
Machine 6, combustion chamber 7, high-pressure turbine 9, low-pressure turbine 10, the first retarder 13 and the second retarder 16；The second level fan 3,
Second retarder 16, compressor 6 and high-pressure turbine 9 etc. form high pressure rotor system, and the high pressure rotor system is supported on second
In bearing 14,5th bearing 18 and 6th bearing 20, the second level fan 3 is connected with one end of the second retarder 16, described
The other end of second retarder 16 is connected with the preceding axle journal 5 of compressor 6, and the high-pressure turbine 9 is supported in 6th bearing 20, institute
It states second bearing 14 and 5th bearing 18 is mounted on Middle casing 4, the 6th bearing 20 is intershaft bearing, is mounted on high pressure
In the rear shaft neck 8 and low-pressure turbine shaft 19 of turbine 9；The 5th bearing 18 is ball bearing, bears the axis of high pressure rotor system
To power and least partially radially power, the second bearing 14 and 6th bearing 20 are stick roller bearing, are primarily subjected to the diameter of system generation
To load；
The first order fan 2, the first retarder 13 and low-pressure turbine 10 etc. form low pressure rotor system, and the low pressure turns
Subsystem is supported in first bearing 12,3rd bearing 15, fourth bearing 17 and 7th bearing 21, the first order fan 2 one
End is mounted in first bearing 12, and the other end is connected with the first retarder 13, before the other end of the first bearing 12 is mounted on
On casing 1, the other end of first retarder 13 is connected by low-pressure turbine shaft 19 with low-pressure turbine 10, the low-pressure turbine
10 are supported in 7th bearing 21, and the 7th bearing 21 is mounted on rear housing 11, and the 3rd bearing 15 is intershaft bearing,
It is mounted between the first retarder 13 and second level fan 3, the fourth bearing 17 is intershaft bearing, is mounted on compressor 6
Between preceding axle journal 5 and low-pressure turbine shaft 19；The first bearing 12 be ball bearing, bear low pressure rotor system axial force and
Least partially radially power, the 3rd bearing 15, fourth bearing 17 and 7th bearing 21 are stick roller bearing, are primarily subjected to system generation
Radial load；
As shown in figure 4, by front housing 1, Middle casing 4, compressor casing 22, combustion chamber 7, outer culvert casing 23, low pressure whirlpool
The stator system of the composition engine such as casing 24, rear housing 11 and jet pipe 25 is taken turns, wherein front housing 1, Middle casing 4 and rear housing
11 3 are main support case, and stator system bears the load generated by each bearing and engine interior gas, maintain entire hair
The steady operation of motivation system.
Embodiment one: in conjunction with attached drawing 1 and Fig. 2, when the engine operates, high pressure rotor system is according to clockwise along course
Direction rotate, since the revolving speed of compressor 6 is higher, second level fan 3 is limited by size, and tangential velocity should not be too large；
The second retarder 16 is devised between compressor 6 and second level fan 3, for the output revolving speed of compressor 6 to be reduced to
The suitable degree of second level fan 3, can give full play to compressor 6 and the respective component advantage of second level fan 3, to mention in this way
The performance of high engine.
Embodiment two: in conjunction with attached drawing 1 and Fig. 3, when the engine operates, low pressure rotor system is according to counterclockwise along course
Direction rotate, since the revolving speed of low-pressure turbine 10 is higher, first order fan 2 is limited by size, and tangential velocity should not mistake
Greatly；The first retarder 13 is devised between low-pressure turbine 10 and first order fan 2, for by the output revolving speed of low-pressure turbine 10
It is reduced to the suitable degree of first order fan 2, low-pressure turbine 10 and the respective component of first order fan 2 can be given full play in this way
Advantage, to improve the performance of engine.
A kind of novel aerial turbo fan engine of the invention is due to using design of the high and low pressure rotor-support-foundation system to turning
Thought eliminates stator guiding between first order fan 2 and second level fan 3, between high-pressure turbine 9 and low-pressure turbine 10
Blade, it is this to design the gyroscopic couple for not only reducing engine, the stability of aircraft is improved, while shortening engine
Axial length alleviates the weight of structure, reduces development cost, improves thrust ratio.
Claims (2)
1. a kind of novel aerial turbo fan engine, which is characterized in that including first order fan, second level fan, compressor,
Combustion chamber, high-pressure turbine, low-pressure turbine, the first retarder and the second retarder, first order fan, the first retarder and low pressure whirlpool
Wheel composition low pressure rotor system, the low pressure rotor system are supported on first bearing, 3rd bearing, fourth bearing and 7th bearing
On, first order fan one end is mounted in first bearing and the other end is connected with the first retarder, and first bearing is mounted on preceding machine
On casket, the other end of the first retarder is connected by low-pressure turbine shaft with low-pressure turbine, and low-pressure turbine is supported in 7th bearing,
7th bearing is mounted on rear housing；3rd bearing and fourth bearing are intershaft bearing, and 3rd bearing is mounted on the first retarder
Between the fan of the second level, fourth bearing is mounted between the preceding axle journal of compressor and low-pressure turbine shaft；Second level fan, second
Retarder, compressor and high-pressure turbine form high pressure rotor system, high pressure rotor system be supported on second bearing, 5th bearing and
In 6th bearing, second level fan is connected with one end of the second retarder, the other end of the second retarder and the front axle of compressor
Neck is connected, and high-pressure turbine is supported in 6th bearing, and second bearing and 5th bearing are mounted on Middle casing；6th bearing is
Intershaft bearing is mounted in the rear shaft neck and low-pressure turbine shaft of high-pressure turbine.
2. novel aerial turbo fan engine according to claim 1, which is characterized in that front housing, Middle casing, pressure
Mechanism of qi casing, combustion chamber, the outer stator system for containing casing, low-pressure turbine casing, rear housing and jet pipe composition engine, wherein before
Casing, Middle casing and rear housing are main support case.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910274675.8A CN109854377A (en) | 2019-04-08 | 2019-04-08 | A kind of novel aerial turbo fan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910274675.8A CN109854377A (en) | 2019-04-08 | 2019-04-08 | A kind of novel aerial turbo fan engine |
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| Publication Number | Publication Date |
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| CN109854377A true CN109854377A (en) | 2019-06-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910274675.8A Pending CN109854377A (en) | 2019-04-08 | 2019-04-08 | A kind of novel aerial turbo fan engine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111305952A (en) * | 2020-02-26 | 2020-06-19 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system based on heating of outer duct |
| CN112983651A (en) * | 2021-04-26 | 2021-06-18 | 黄锴 | Small-size aviation birotor unmanned aerial vehicle engine |
| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113864239A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
| CN115405421A (en) * | 2022-11-01 | 2022-11-29 | 北京航空航天大学 | Three-rotor variable-cycle engine overall structure with interstage combustion chamber |
| CN116085142A (en) * | 2023-04-11 | 2023-05-09 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1453466A (en) * | 2002-03-01 | 2003-11-05 | 通用电气公司 | Reverse rotary aero-gas turbine of air-compressor with high general pressure ratio |
| US20050081509A1 (en) * | 2003-10-20 | 2005-04-21 | Johnson James E. | Flade gas turbine engine with fixed geometry inlet |
| CN1900508A (en) * | 2005-06-06 | 2007-01-24 | 通用电气公司 | Integrated counterrotating turbofan |
| CN101149026A (en) * | 2007-11-08 | 2008-03-26 | 北京航空航天大学 | Turbine fan engine and design method thereof |
| US20130004297A1 (en) * | 2007-10-03 | 2013-01-03 | Sheridan William G | Dual fan gas turbine engine and gear train |
| CN103953445A (en) * | 2014-05-15 | 2014-07-30 | 中国船舶重工集团公司第七�三研究所 | Multi-rotor gas generator provided with counter rotating gas compressors |
| CN105765166A (en) * | 2013-11-21 | 2016-07-13 | 斯奈克玛 | Modular engine, such as a jet engine, with a speed reduction gear |
| EP3112613A1 (en) * | 2015-07-01 | 2017-01-04 | United Technologies Corporation | Geared turbofan fan turbine engine architecture |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN209621470U (en) * | 2019-04-08 | 2019-11-12 | 沈阳建筑大学 | A kind of novel aerial turbo fan engine |
-
2019
- 2019-04-08 CN CN201910274675.8A patent/CN109854377A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1453466A (en) * | 2002-03-01 | 2003-11-05 | 通用电气公司 | Reverse rotary aero-gas turbine of air-compressor with high general pressure ratio |
| US20050081509A1 (en) * | 2003-10-20 | 2005-04-21 | Johnson James E. | Flade gas turbine engine with fixed geometry inlet |
| CN1900508A (en) * | 2005-06-06 | 2007-01-24 | 通用电气公司 | Integrated counterrotating turbofan |
| US20130004297A1 (en) * | 2007-10-03 | 2013-01-03 | Sheridan William G | Dual fan gas turbine engine and gear train |
| CN101149026A (en) * | 2007-11-08 | 2008-03-26 | 北京航空航天大学 | Turbine fan engine and design method thereof |
| CN105765166A (en) * | 2013-11-21 | 2016-07-13 | 斯奈克玛 | Modular engine, such as a jet engine, with a speed reduction gear |
| CN103953445A (en) * | 2014-05-15 | 2014-07-30 | 中国船舶重工集团公司第七�三研究所 | Multi-rotor gas generator provided with counter rotating gas compressors |
| EP3112613A1 (en) * | 2015-07-01 | 2017-01-04 | United Technologies Corporation | Geared turbofan fan turbine engine architecture |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN209621470U (en) * | 2019-04-08 | 2019-11-12 | 沈阳建筑大学 | A kind of novel aerial turbo fan engine |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN111305952A (en) * | 2020-02-26 | 2020-06-19 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system based on heating of outer duct |
| CN112983651A (en) * | 2021-04-26 | 2021-06-18 | 黄锴 | Small-size aviation birotor unmanned aerial vehicle engine |
| CN112983651B (en) * | 2021-04-26 | 2023-07-28 | 黄锴 | Small aviation double-rotor unmanned aerial vehicle engine |
| CN113864239A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
| CN115405421A (en) * | 2022-11-01 | 2022-11-29 | 北京航空航天大学 | Three-rotor variable-cycle engine overall structure with interstage combustion chamber |
| CN115405421B (en) * | 2022-11-01 | 2023-02-03 | 北京航空航天大学 | Three-rotor variable-cycle engine overall structure with interstage combustion chamber |
| CN116085142A (en) * | 2023-04-11 | 2023-05-09 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
| CN116085142B (en) * | 2023-04-11 | 2023-05-30 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
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