CN105003339B - Radial multistage turbine engine - Google Patents
Radial multistage turbine engine Download PDFInfo
- Publication number
- CN105003339B CN105003339B CN201510409259.6A CN201510409259A CN105003339B CN 105003339 B CN105003339 B CN 105003339B CN 201510409259 A CN201510409259 A CN 201510409259A CN 105003339 B CN105003339 B CN 105003339B
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- Prior art keywords
- turbine
- main shaft
- compressor
- quiet disk
- disc
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Abstract
The invention discloses a radial multistage turbine engine which is characterized in that an air compressor moving disc is fixed on a main shaft; an air inlet passage is formed in the air compressor moving disc and surrounds the main shaft; multistage moving blades are mounted on two disc surfaces in the radial direction from inside to outside in a step-by-step shortened manner; an air compressor outer stator disc is arranged on the main shaft and is in sealing normal running fit with the air compressor moving disc; an air compressor inner stator disc is rotationally mounted on the other side of the air compressor moving disc; air compressor stator blades in clearance fit with the air compressor moving blades are arranged on the two stator discs respectively; an air inlet is formed in the air compressor outer stator disc; a turbine inner stator disc is rotationally mounted on the main shaft behind the air compressor inner stator disc; a turbine outer stator disc is rotationally mounted at the rear end of the main shaft; a turbine is internally provided with a combustion chamber; a circle of arc sealing wall is connected between the turbine inner stator disc and the circumference wall of the air compressor outer stator disc; a high-pressure air inlet passage is formed in a turbine moving disc and surrounds the main shaft; and moving blades and stator blades are mounted among the turbine moving disc, the turbine outer stator disc and the turbine inner stator disc. The manufacturing cost is reduced.
Description
Technical field：
The present invention relates to electromotor, particularly a kind of suitable for various radial multi-stage propeller for turboprop mechanically installed and used
Machine.
Background technology：
Existing turbogenerator is axial multistage structure mostly, and have radial structure is also radial direction single step arrangement.Axially
Multiple-runner turbine is well suited for using on aviation machine, is not suitable for general big machinery because of its slender construction and high rotating speed
Use with vehicular traffic, in addition because blade there will be certain distortion to leaf top from blade root, there is manufacture difficulty greatly, cost
Height, the shortcoming of low-speed performance difference.
The content of the invention：
It is an object of the invention to provide a kind of simple structure, low cost, being adapted in various radial multi-stages for mechanically using
Turbogenerator.
The technical scheme is that what is completed as follows, radial multi-stage turbogenerator, it is characterised in that：It is
A compressor Moving plate is fixed with key on a main shaft, inlet channel is provided with around main shaft on the disk, the two of the disk
Multistage movable vane piece is provided with by interior shortening step by step outward radially in card, is sealed with compressor Moving plate by outfan on main shaft
It is rotatably assorted and the outer quiet disk of a compressor is installed, compressor Moving plate opposite side is rotatablely equipped with quiet disk in a compressor,
Two Jing Panshang that calm the anger are respectively equipped with the compressor stator piece coordinated with compressor blade and blade gap, in calming the anger for main shaft outfan
The outer quiet disk of machine is provided with air inlet of the loop diameter more than inlet channel, is rotatablely equipped with compressor on the main shaft of quiet disk back
One with diameter greater than quiet disk in the turbine equal to quiet disk in compressor, the rear end thereof of main shaft be provided with one with diameter greater than
Equal to the outer quiet disk of the turbine of quiet disk in compressor, in turbine in quiet disk and compressor between the outer card of quiet disk from main shaft one
Set a distance installs combuster with support between card external diameter, is evenly equipped with passage in the periphery of combustor, in turbine
The outwardly arc sealed wall of a circle is connected between interior quiet disk and the outer quiet disk circumferential wall of compressor, it is quiet inside and outside turbine
A turbine moving plate is fixed with main shaft between disk, high pressure gas passage is provided with around main shaft on turbine moving plate, in whirlpool
Gap is installed between the Moving plate of turbine and inside and outside quiet disk and coordinates the turbine moving blade and Turbomachinery for radially outward increasing one by one
Piece, leaves the compressed gas passage to combustor supply on the inside of arc sealed wall, is provided with fuel on the cylindrical wall of combustor
Nozzle.The outfan of main shaft can as needed from calming the anger generator terminal or turbine end stretches out.
The axial multistage structure of compressor and turbine is changed to radial multi-stage structure by the present invention, makes the length of axle contract significantly
Short, volume is less, and the outside jet torque of turbine circumference is bigger, and high low-speed performance is all good, is easy to match on slow-speed of revolution equipment,
Blade completely dispenses with distortion, also reduces manufacture difficulty, and multistage blade shares a leaf dish and has been greatly reduced manufacturing cost.
Description of the drawings：
Fig. 1 is the structural representation of the present invention；Fig. 2 is the Moving plate overlooking the structure diagram of the turbine of the present invention.
Specific embodiment：
Embodiment is described in detail with reference to accompanying drawing, and the present invention is on a main shaft 12 one to be fixed near outfan key
Compressor Moving plate 7, is provided with inlet channel 13 around main shaft on the disk, in two cards of the disk radially by it is interior outward step by step
Shorten and multistage movable vane piece 6 is installed, being rotatably assorted by outfan and Moving plate sealing on main shaft, it is outer quiet to be provided with a compressor
Disk 10, is rotatablely equipped with quiet disk 14 in a compressor in compressor Moving plate opposite side, is set on the quiet disk of two compressors respectively
There is the compressor stator piece 9 coordinated with compressor blade and blade gap, a circle is provided with the outer quiet disk of compressor of main shaft outfan
With diameter greater than the air inlet 11 of inlet channel, one is rotatablely equipped with compressor on the main shaft of quiet disk back with diameter greater than being equal to
Quiet disk 5 in the turbine of quiet disk in compressor, the rear end thereof of main shaft be provided with one it is quiet with diameter greater than equal in compressor
The outer quiet disk 1 of the turbine of disk, in turbine in quiet disk and compressor between the outer card of quiet disk with a certain distance from main shaft to card
With supporting 18 to install combuster 17 between external diameter, passage 19 is evenly equipped with the periphery of combustor, the quiet disk in turbine
The outwardly arc sealed wall 8 of a circle is connected between the outer quiet disk circumferential wall of compressor, inside and outside turbine quiet disk it
Between main shaft on be fixed with a turbine moving plate 2, be provided with high pressure gas passage 20 around main shaft on turbine moving plate, in turbine
Gap is installed between the Moving plate of machine and inside and outside quiet disk and coordinates the turbine moving blade 3 and turbine stator vane for radially outward increasing one by one
4, the compressed gas passage 16 to combustor supply is left on the inside of arc sealed wall, fuel is installed on the cylindrical wall of combustor
Nozzle 15.The outfan of main shaft can as needed from calming the anger generator terminal or turbine end stretches out.
The axial multistage structure of compressor and turbine is changed to radial multi-stage structure by the present invention, and combustor is also by axially tying
Structure is changed to radial structure, greatly shortens elongated main shaft first, profile near cubic, the outside jet power of circumference of turbine
Square is bigger, can make low-speed big, easily matches with slow-speed of revolution equipment, is particularly well-suited to tank, car, truck,
Use in the plant equipment such as excavator, loader electromotor.There is easy to manufacture, low cost, applied widely.
Claims (2)
1. radial multi-stage turbogenerator, it is characterised in that：It is on a main shaft to be fixed with a compressor Moving plate with key,
Inlet channel is provided with around main shaft on the disk, in two cards of the disk radially by it is interior shorten step by step outward be provided with it is multistage
Movable vane piece, is rotatably assorted by outfan and the sealing of compressor Moving plate on main shaft and is provided with the outer quiet disk of a compressor, compressor
Moving plate opposite side is rotatablely equipped with quiet disk in a compressor, is respectively equipped with between compressor blade and blade in two Jing Panshang that calm the anger
The compressor stator piece that gap coordinates, is provided with a loop diameter entering more than inlet channel on the outer quiet disk of compressor of main shaft outfan
QI KOU, is rotatablely equipped with one in compressor with diameter greater than in the turbine equal to quiet disk in compressor on the main shaft of quiet disk back
Quiet disk, is provided with one with diameter greater than the outer quiet disk of turbine equal to quiet disk in compressor in the rear end thereof of main shaft, in turbine
Burning is installed with support between card external diameter with a certain distance from main shaft between the outer card of quiet disk in quiet disk and compressor in machine
Room, is evenly equipped with passage in the periphery of combustor, is connected with turbine between quiet disk and the outer quiet disk circumferential wall of compressor
The outwardly arc sealed wall of one circle, is fixed with a turbine moving plate on the main shaft inside and outside turbine between quiet disk,
High pressure gas passage is provided with around main shaft on turbine moving plate, gap is installed between the Moving plate and inside and outside quiet disk of turbine and is matched somebody with somebody
Turbine moving blade and turbine stator vane that conjunction radially outward increases one by one, leave to combustor supply on the inside of arc sealed wall
Compressed gas passage, is provided with fuel burner on the cylindrical wall of combustor.
2. radial multi-stage turbogenerator according to claim 1, it is characterised in that：The outfan of main shaft can be as needed
From calming the anger generator terminal or turbine end stretches out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510409259.6A CN105003339B (en) | 2015-07-14 | 2015-07-14 | Radial multistage turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510409259.6A CN105003339B (en) | 2015-07-14 | 2015-07-14 | Radial multistage turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105003339A CN105003339A (en) | 2015-10-28 |
| CN105003339B true CN105003339B (en) | 2017-04-12 |
Family
ID=54376161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510409259.6A Active CN105003339B (en) | 2015-07-14 | 2015-07-14 | Radial multistage turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105003339B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB284116A (en) * | 1927-04-30 | 1928-01-26 | Alfred Bonom | Improvements in turbines |
| CN1191278A (en) * | 1997-02-17 | 1998-08-26 | 川崎重工业株式会社 | Centrifugal multivane blower |
| CN1196107A (en) * | 1995-09-08 | 1998-10-14 | 本田技研工业株式会社 | Gas-turbine engine |
| CN1279742A (en) * | 1997-10-24 | 2001-01-10 | 罗伯特·G·詹姆斯 | Improved turbine powerplant |
| EP1574676A2 (en) * | 2004-03-04 | 2005-09-14 | Technical Directions Inc. (TDI) | Turbine machine |
| CN204984604U (en) * | 2015-07-14 | 2016-01-20 | 张耀明 | Radial multistage turbine engine |
-
2015
- 2015-07-14 CN CN201510409259.6A patent/CN105003339B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB284116A (en) * | 1927-04-30 | 1928-01-26 | Alfred Bonom | Improvements in turbines |
| CN1196107A (en) * | 1995-09-08 | 1998-10-14 | 本田技研工业株式会社 | Gas-turbine engine |
| CN1191278A (en) * | 1997-02-17 | 1998-08-26 | 川崎重工业株式会社 | Centrifugal multivane blower |
| CN1279742A (en) * | 1997-10-24 | 2001-01-10 | 罗伯特·G·詹姆斯 | Improved turbine powerplant |
| EP1574676A2 (en) * | 2004-03-04 | 2005-09-14 | Technical Directions Inc. (TDI) | Turbine machine |
| CN204984604U (en) * | 2015-07-14 | 2016-01-20 | 张耀明 | Radial multistage turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105003339A (en) | 2015-10-28 |
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