CN107882635A - A kind of aero gas turbine engine - Google Patents
A kind of aero gas turbine engine Download PDFInfo
- Publication number
- CN107882635A CN107882635A CN201610874366.0A CN201610874366A CN107882635A CN 107882635 A CN107882635 A CN 107882635A CN 201610874366 A CN201610874366 A CN 201610874366A CN 107882635 A CN107882635 A CN 107882635A
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- China
- Prior art keywords
- planetary gear
- gear
- planet carrier
- pressure
- external toothing
- Prior art date
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Classifications
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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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)
- Retarders (AREA)
Abstract
It is an object of the invention to provide a kind of aero gas turbine engine, the fan and low-pressure compressor of the aero gas turbine engine extract power by gear-box from high-pressure turbine, so as to cancel the low-pressure turbine of aero gas turbine engine.Aero gas turbine engine includes high pressure rotor, fan propeller, low-pressure compressor and gear-box, gear-box includes sun gear, planetary gear, planet carrier and external toothing, planetary gear sets around sun gear and engaged with sun gear, external toothing sets around planetary gear and engaged with planetary gear, keeps fixing in planetary gear installation planet carrier and relative to planet carrier；The number of teeth of sun gear is less than the number of teeth of external toothing；High pressure rotor is connected with sun gear, and fan propeller is connected with planet carrier, and low-pressure compressor is connected with external toothing.
Description
Technical field
The present invention relates to aviation field, relates more specifically to a kind of aero gas turbine engine.
Background technology
Traditional twin shaft directly drives turbofan rotor main will be by fan, low-pressure compressor, high-pressure compressor, high pressure
Turbine, low-pressure turbine composition, wherein high-pressure compressor and high-pressure turbine connect into high pressure rotor, fan, low-pressure compressor and low
Pressure turbine connects to form low pressure rotor.In the high bypass ratio bus engine of high thrust, fan and low-pressure compressor are jointly by low
Turbine direct drive is pressed, 3~5 grades of low-pressure compressors is designed with after fan propeller, is to improve the overall pressure tatio of engine and sky
Throughput.Due to being limited by fan tangential velocity, low-pressure compressor and low-pressure turbine can only work together with fan propeller
Under relatively low rotating speed.So, low-pressure compressor and turbine not operate under optimum speed, limit the work of low-pressure compressor
Make ability, and make it that the series of low-pressure turbine is more, low-pressure turbine series increases, it is meant that the increase of engine weight.
However, engine weight problem is also a big restraining factors of current development of engine.
For aero-engine, high overall pressure tatio, high bypass ratio and low consumption oil cut rate are the high performance important indicators of engine.Carry
High overall pressure tatio and reduction low-pressure turbine series are the bottlenecks of alternate-engine development.If the premise of traditional structure can not overturned
Under, reach raising engine overall pressure tatio by changing partial structurtes, or even engine weight is reduced, this will bring very to aircraft industry
Good prospect.
The content of the invention
It is an object of the invention to provide a kind of aero gas turbine engine, the fan of the aero gas turbine engine
Power is extracted from high-pressure turbine by gear-box with low-pressure compressor, so as to cancel the low pressure of aero gas turbine engine
Turbine.
To realize the aero gas turbine engine of the purpose, including high pressure rotor, fan propeller, low-pressure compressor and
Gear-box, the gear-box include sun gear, planetary gear, planet carrier and external toothing, and the planetary gear is set around the sun gear
Put and engaged with the sun gear, the external toothing sets around the planetary gear and engaged with the planetary gear, described
Planetary gear is arranged on the planet carrier and keeps fixing relative to the planet carrier；The number of teeth of the sun gear is outer less than described
The number of teeth of gear ring；
The high pressure rotor is connected with the sun gear, and the fan propeller is connected with the planet carrier, the low pressure pressure
Mechanism of qi is connected with the external toothing；
The rotating speed of the fan propeller is identical with the size and Orientation of the planet carrier rotating speed, and the low-pressure compressor turns
It is fast identical with the size and Orientation of the external toothing rotating speed；
The high pressure rotor can drive the sun gear rotation, and the sun gear can drive the planetary gear to surround institute
Sun gear revolution is stated, the direction of the planetary gear revolution is in opposite direction with the sun gear rotation；
The planet carrier can follow the planetary gear to be rotated around the sun gear, and the planet carrier rotating speed
Size and Orientation it is identical with the size and Orientation of the planetary gear revolution speed；
The planetary gear can drive the external toothing to be rotated, and the size of the external toothing rotating speed is more than described
The velocity magnitude of planetary gear revolution, the direction that the external toothing rotates are identical with the direction of the planetary gear revolution.
Described aero gas turbine engine, its further feature are that the aero gas turbine engine also wraps
High-pressure turbine and high-pressure compressor are included, the high-pressure turbine connects to form the high pressure rotor with the high-pressure compressor.
Described aero gas turbine engine, its further feature are that the aero gas turbine engine also wraps
High-pressure turbine and high-pressure compressor are included, the high-pressure turbine connects to form the high pressure rotor with the high-pressure compressor.
Described aero gas turbine engine, its further feature are that the quantity of the planetary gear is five, and
It is uniformly distributed along the circumference of the sun gear.
Described aero gas turbine engine, its further feature are that the planetary gear is one with the planet carrier
Body formed manufacture.
Described aero gas turbine engine, its further feature are that the planet carrier leads to the fan propeller
Cross bearing connection.
The positive effect of the present invention is：Aero gas turbine engine provided by the invention, its fan and low pressure
Compressor can extract power by gear-box from high-pressure turbine, so as to cancel the low pressure whirlpool of aero gas turbine engine
Wheel, so as to mitigate engine weight, shorten engine overall length, reduce engine volume.Fan propeller and low-pressure compressor
Rotor speed is controlled by high pressure rotor respectively, and the mutual rotating ratio between rotor is controlled by gear box ratio.Fan propeller can be with
Compared with independent operation under the slow-speed of revolution, ensureing the tangential velocity of fan.Fan forced level rotor can be under higher optimum speed
Independent operation, low-pressure compressor gearratio can be improved, further improve engine overall pressure tatio.
Brief description of the drawings
The above and other features of the present invention, property and advantage will pass through retouching with reference to the accompanying drawings and examples
State and become readily apparent from, wherein：
Fig. 1 is the schematic diagram of aero gas turbine engine in comparative example；
Fig. 2 is the schematic diagram of aero gas turbine engine in the present invention；
Fig. 3 is the enlarged drawing at A in Fig. 2；
Fig. 4 is the theory of engagement figure of middle gear case of the present invention.
Embodiment
With reference to specific embodiments and the drawings, the invention will be further described, elaborates in the following description more
Details to facilitate a thorough understanding of the present invention, still the present invention obviously can be come with a variety of other manners different from this description it is real
Apply, those skilled in the art can make similar popularization according to practical situations in the case of without prejudice to intension of the present invention, drill
Unravel silk, therefore should not be limited the scope of the invention with the content of this specific embodiment.
It should be noted that Fig. 1 to Fig. 4 only as an example, its not be according to equal proportion condition draw, and
It should not be construed as limiting in this, as the protection domain to actual requirement of the present invention.
As shown in figure 1, in a comparative example, aero gas turbine engine 100 is by fan 101, low-pressure compressor
102nd, casing 107, low-pressure turbine between Middle casing 103, high-pressure compressor 104, combustion chamber 105, high-pressure turbine 106, stage of turbine
108 and turbine rear casing 109 this several big parts composition.Wherein, fan 101, low-pressure compressor 102 and low-pressure turbine 108 connect
Form low pressure rotor 110, fan 101 and low-pressure compressor rotor and extract power rotation, high-pressure compressor from low-pressure turbine 108
104 and the connection of high-pressure turbine 106 form high pressure rotor 111, high-pressure compressor 104 extracts power from high-pressure turbine 106 and rotated.
With continued reference to Fig. 1, fan 101 and low-pressure compressor 102 link into an integrated entity and have an identical rotating speed, due to by
The limitation of the tangential velocity of fan 101, low-pressure compressor 102 and low-pressure turbine 108 can only be operated in relatively low together with fan 101
Under rotating speed.So, low-pressure compressor 102 not operates under optimum speed, limits the ability to work of low-pressure compressor 102,
Cause that the series of low-pressure turbine 108 is more simultaneously, the series of low-pressure turbine 108 increases, it is meant that the increase of engine weight.
To solve the above problems, in one embodiment of the present of invention, there is provided a kind of following aero gas turbine engine
200.Aero gas turbine engine 200 eliminates low-pressure turbine.
Specifically, aero gas turbine engine 200 includes high pressure rotor 218, fan propeller 219, low-pressure compressor 202
With gear-box 208, gear-box 208 includes sun gear 209, planetary gear 210, planet carrier 212 and external toothing 211, and planetary gear 210 encloses
Set around sun gear 209 and engaged with sun gear 209, external toothing 211 set around planetary gear 210 and with planetary gear 210
Engagement, planetary gear 210 are installed in planet carrier 212 and keep fixing relative to planet carrier 212；The number of teeth of sun gear 209 is less than
The number of teeth of external toothing 211；Planetary gear 210 can be by being integrally formed manufacture with planet carrier 212 so that planetary gear 210 is relative to row
Carrier 212 does not rotate, so as to avoid planetary gear 210 that rotation occurs.It can also be set between planetary gear 210 and planet carrier 212
Put locking mechanism so that planetary gear 210 does not rotate relative to planet carrier 212, so as to avoid planetary gear 210 that rotation occurs.
High pressure rotor 218 is connected with sun gear 209, and fan propeller 219 is connected with planet carrier 212, low-pressure compressor 202 with
External toothing 211 connects；Alternatively, planet carrier 212 is connected with fan propeller 219 by bearing 220.
The rotating speed of fan propeller 219 is identical with the size and Orientation of the rotating speed of planet carrier 212, the rotating speed of low-pressure compressor 202
It is identical with the size and Orientation of the rotating speed of external toothing 211；
High pressure rotor 218 can drive the rotation of sun gear 209, and sun gear 209 can drive planetary gear 210 to surround sun gear
209 revolution, the direction that planetary gear 210 revolves round the sun are in opposite direction with the rotation of sun gear 209；
Planet carrier 212 can be rotated with planet wheels 210 around sun gear 209, and the rotating speed of planet carrier 212 is big
Small and direction is identical with the size and Orientation of the revolution speed of planetary gear 210；
Planetary gear 210 can drive external toothing 211 to be rotated, and the size of the rotating speed of external toothing 211 is more than planetary gear
The velocity magnitude of 210 revolution, the direction that external toothing 211 rotates are identical with the direction that planetary gear 210 revolves round the sun.
Aero gas turbine engine also includes high-pressure turbine 206 and high-pressure compressor 204, high-pressure turbine 206 and high pressure
The connection of compressor 204 forms high pressure rotor 218.Alternatively, the quantity of planetary gear 210 is five, and along the week of sun gear 209
To being uniformly distributed.
With continued reference to Fig. 2, aero gas turbine engine also includes Middle casing 203, combustion chamber 205 and turbine rear casing
207.Gear-box 208 is arranged between fan 201 and high-pressure compressor 204, and high-pressure compressor 204 is formed with high-pressure turbine 206
High pressure rotor 218, high pressure rotor 218 are supported on bearing 215 and bearing 216, and high pressure rotor 218 is connected with sun gear 209, are made
Inputted for the power of gear-box；The cantilever support of fan propeller 219 is on bearing 213 and bearing 217, fan propeller 219 and low pressure
Compressor 202 is supported on bearing 213 and bearing 214, and fan propeller is connected with planet carrier；The front end of low-pressure compressor 202 supports
On bearing 213, rear end be supported on bearing 214, low-pressure compressor 202 is connected with external toothing 211.High pressure rotor 218 supports
On bearing 215 and bearing 216.
The drive connection and principle of gear-box of the present invention are as follows, as shown in figure 3, in planetary gear train, high pressure rotor 218 drives
The dynamic rotation of sun gear 209, sun gear 209 can drive planetary gear 210 to be revolved round the sun around sun gear 209, the side that planetary gear 210 revolves round the sun
To in opposite direction with the rotation of sun gear 209；Planet carrier 212 can be rotated with planet wheels 210 around sun gear 209,
And the size and Orientation of the rotating speed of planet carrier 212 is identical with the size and Orientation of the revolution speed of planetary gear 210；The energy of planetary gear 210
Enough driving external toothings 211 are rotated, and the size of the rotating speed of external toothing 211 is more than the velocity magnitude that planetary gear 210 revolves round the sun, outside
The direction that gear ring 211 rotates is identical with the direction that planetary gear 210 revolves round the sun.
Because planetary gear 210 is used as idler gear all the time, their number of teeth is unrelated with the gearratio of gear-box 208.Planet
210, wheel is revolved round the sun, without rotation.Therefore, the gearratio of gear-box 208 depends on planet carrier 212, the and of external toothing 211
The number of teeth of sun gear 209, because planet carrier 212 does not have tooth, one virtual tooth is specified to planet carrier 212 when calculating gearratio
Number.In the present invention, the number of teeth of planet carrier 212 is equal to the number of teeth of sun gear 209 and the number of teeth sum of external toothing 211.Because pass
The dynamic ratio than being equal to the slave unit number of teeth and the driving part number of teeth, therefore in the planetary gear train, sun gear 209, external toothing
211st, the number of teeth increases successively between planet carrier 212, and rotating speed reduces successively.The rotating speed of fan propeller 219 and the rotating speed of planet carrier 212
Size and Orientation is identical, because the rotating speed of low-pressure compressor 202 is identical therefore low with the size and Orientation of the rotating speed of external toothing 211
The rotating speed of compressor 202 is pressed to be more than the rotating speed of fan propeller 219.
According to this relation, the number of teeth of external toothing 211 and sun gear 209 is adjusted, equivalent to adjusting planet carrier 212 simultaneously
The number of teeth, so as to have adjusted the gearratio of gear-box 208.It can so ensure that fan propeller 219 is transported under relatively low optimum speed
Turn, low-pressure compressor 202 operates under higher optimum speed.
The positive effect of the present invention is：Aero gas turbine engine provided by the invention, its fan and low pressure
Compressor can extract power by gear-box from high-pressure turbine, so as to cancel the low pressure whirlpool of aero gas turbine engine
Wheel, to mitigate engine weight, shorten engine overall length, reduce engine volume.Fan propeller and low-pressure compressor rotor turn
Speed is controlled by high pressure rotor respectively, and the mutual rotating ratio between rotor is controlled by gear box ratio.Fan propeller can be relatively low
Independent operation under rotating speed, ensure the tangential velocity of fan.Fan forced level rotor can independently be transported under higher optimum speed
Turn, low-pressure compressor gearratio can be improved, further improve engine overall pressure tatio.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this area skill
Art personnel without departing from the spirit and scope of the present invention, can make possible variation and modification, every without departing from this hair
The content of bright technical scheme, any modification that the technical spirit according to the present invention is made to above example, equivalent variations and repair
Decorations, each fall within the protection domain that the claims in the present invention are defined.
Claims (5)
1. a kind of aero gas turbine engine, it is characterised in that including high pressure rotor (218), fan propeller (219), low pressure
Compressor (202) and gear-box (208), the gear-box (208) include sun gear (209), planetary gear (210), planet carrier
(212) and external toothing (211), the planetary gear (210) set around the sun gear (209) and with the sun gear
(209) engage, the external toothing (211) sets and engaged with the planetary gear (210), institute around the planetary gear (210)
Planetary gear (210) is stated on the planet carrier (212) and keeps fixing relative to the planet carrier (212)；The sun
The number of teeth for taking turns (209) is less than the number of teeth of the external toothing (211)；
The high pressure rotor (218) is connected with the sun gear (209), the fan propeller (219) and the planet carrier (212)
Connection, the low-pressure compressor (202) are connected with the external toothing (211)；
The rotating speed of the fan propeller (219) is identical with the size and Orientation of the planet carrier (212) rotating speed, and the low pressure is calmed the anger
The rotating speed of machine (202) is identical with the size and Orientation of the external toothing (211) rotating speed；
The high pressure rotor (218) can drive the sun gear (209) rotation, and the sun gear (209) can drive described
Planetary gear (210) revolves round the sun around the sun gear (209), the direction of planetary gear (210) revolution and the sun gear (209)
Rotation it is in opposite direction；
The planet carrier (212) can follow the planetary gear (210) to be rotated around the sun gear (209), and institute
The size and Orientation for stating planet carrier (212) rotating speed is identical with the size and Orientation of the planetary gear (210) revolution speed；
The planetary gear (210) can drive the external toothing (211) to be rotated, and the external toothing (211) rotating speed
Size is more than the velocity magnitude of the planetary gear (210) revolution, the direction that the external toothing (211) rotates and the planetary gear
(210) direction of revolution is identical.
2. aero gas turbine engine as claimed in claim 1, it is characterised in that the aero gas turbine engine is also
Including high-pressure turbine (206) and high-pressure compressor (204), the high-pressure turbine (206) and the high-pressure compressor (204) connection
Form the high pressure rotor (218).
3. aero gas turbine engine as claimed in claim 1, it is characterised in that the quantity of the planetary gear (210) is
Five, and be uniformly distributed along the circumference of the sun gear (209).
4. aero gas turbine engine as claimed in claim 1, it is characterised in that the planetary gear (210) and the row
Carrier (212) is formed in one manufacture.
5. aero gas turbine engine as claimed in claim 1, it is characterised in that the planet carrier (212) and the wind
Rotor (219) is fanned to connect by bearing (220).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610874366.0A CN107882635A (en) | 2016-09-30 | 2016-09-30 | A kind of aero gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610874366.0A CN107882635A (en) | 2016-09-30 | 2016-09-30 | A kind of aero gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107882635A true CN107882635A (en) | 2018-04-06 |
Family
ID=61769589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610874366.0A Pending CN107882635A (en) | 2016-09-30 | 2016-09-30 | A kind of aero gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107882635A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111706432A (en) * | 2020-05-28 | 2020-09-25 | 中国航发湖南动力机械研究所 | Novel paddle fan engine and propulsion device with same |
-
2016
- 2016-09-30 CN CN201610874366.0A patent/CN107882635A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111706432A (en) * | 2020-05-28 | 2020-09-25 | 中国航发湖南动力机械研究所 | Novel paddle fan engine and propulsion device with same |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180406 |
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| WD01 | Invention patent application deemed withdrawn after publication |