CN108952964A - A kind of gas-turbine unit of single composite impeller - Google Patents
A kind of gas-turbine unit of single composite impeller Download PDFInfo
- Publication number
- CN108952964A CN108952964A CN201810770399.XA CN201810770399A CN108952964A CN 108952964 A CN108952964 A CN 108952964A CN 201810770399 A CN201810770399 A CN 201810770399A CN 108952964 A CN108952964 A CN 108952964A
- Authority
- CN
- China
- Prior art keywords
- main shaft
- annular
- case component
- composite impeller
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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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
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
-
- 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
- F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
-
- 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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
Abstract
The invention discloses a kind of gas-turbine units of single composite impeller, specifically include that composite impeller, main shaft, starting motor, clutch, bearing, rectification bracket, annular swirl combustion chamber, annular case component, tail cone, jet pipe that centrifugal compressor blade and hollow turbine vane are combined into one, main shaft is connected firmly with composite impeller, starter motor is connect by clutch with main shaft, main shaft is mounted in axle sleeve by two bearings, rectification bracket is connected with annular case component, has installation clip to be fixed on aircraft on annular case component.Annular swirl combustion chamber is located in toroidal shell component, and tail cone is located at impeller rear portion, and jet pipe and housing unit are connected to an entirety.It is an advantage of the invention that engine structure is simplified, weight saving, improves rotor machinery rotating property, reduces cost, moreover it is possible to efficiently use compressed air stream and cool to hollow turbine vane, further increase engine performance and service life.
Description
Technical field
The present invention relates to gas turbine fields, more particularly to a kind of gas-turbine unit of single composite impeller.
Background technique
In aviation field, with the development of aeronautical technology, unmanned plane and light aerocraft gradually become the production of most attraction
One of product, however the light high-efficiency of power device is the key technology for restricting above-mentioned aircraft development.Small turbogenerator
Demand and development be getting faster be aero-engine an important branch, predominantly unmanned plane, cruise missile, light aerocraft etc.
Power needed for providing, or ground installation provides electric power and power etc..Common small turbogenerator is mainly by one
It is driven axis connection centrifugal compressor and radial turbine or axial-flow turbine forms a rotor rotatable parts, tiny rotor turns
Fast height, span are big, and rotor running accuracy and stability of vibration are difficult to control.Simultaneously because infrastructure cost limitation reason, common
Small engine is the service life that turbine greatly reduces in this way without cooling and the performance of engine for turbine,
Its development and application is seriously affected.In view of the above-mentioned problems, the compound leaf of small turbogenerator that one kind proposed by the present invention is novel
Compressor and turbine are combined into one by wheel construction, enormously simplify rotor structure, alleviate weight, reduce cost, are improved
Rotor machinery rotating property.Compressed air stream can also be effectively utilized simultaneously to cool down turbine wheel, thus to improve
Turbine inlet temperature or reduction turbine material require to create condition, and are conducive to further increase engine performance and service life.
Summary of the invention
In order to solve the above-mentioned technical problems, the present invention provides a kind of gas-turbine units of single composite impeller.
The present invention adopts the following technical scheme: a kind of gas-turbine unit of single composite impeller, including starting motor,
Clutch, main shaft, bearing, rectification bracket, centrifugal compressor blade and hollow turbine vane are smoothly connected the compound leaf being integrated
Wheel, annular turbulence-type combustion chamber, annular case component, tail cone, jet pipe, the outer rim radial passage of centrifugal compressor blade with
Hollow turbine vane, which is smoothly connected, collectively constitutes one with the composite impeller calmed the anger with expansion work dual function, starts motor
It is connected by clutch with main shaft one end, the other end of main shaft is fixedly connected with the centrifugal compressor blade in composite impeller, institute
It states outer surface on the right side of starting motor and uniformly connects three connecting rod one end, the connecting rod other end is fixedly connected with rectification bracket, from
Clutch, main shaft, bearing are located in axle sleeve, and main shaft both ends are arranged bearing, and sleeve outer surface is uniformly provided with three rectification brackets, axle sleeve
Outer surface and rectification bracket one end are welded, and the rectification bracket other end is fixedly connected with annular case component, annular spiral-flow type combustion
It burns room to be located in annular case component, annular case component inner ring is connected with annular turbulence-type combustion chamber inner ring, the annular rotation
Streaming combustion chamber is held and fired in the relaying continuation of insurance of annular turbulence-type combustion chamber by the peripheral speed of centrifugal compressor blade exit air-flow
It burns and directly drives hollow turbine vane after heating accelerates, hollow turbine vane rotation drives the rotation of centrifugal compressor blade, annular
Case component right side is fixedly connected with jet pipe, and tail cone is located at centrifugal compressor bucket rear, and is connected to jet pipe
One entirety, the annular case component is equipped with clip, for the gas-turbine unit of single composite impeller to be fixed to
On aircraft.
Working principle: the outer rim radial passage of centrifugal compressor blade and hollow turbine vane are smoothly connected altogether by the present invention
There is the composite impeller calmed the anger with expansion work dual function with composition one, annular turbulence-type combustion chamber is by centrifugal compressor leaf
Hollow turbine vane is held and driven to the peripheral speed of piece exit flow in the relaying continuation of insurance of annular turbulence-type combustion chamber, main shaft with it is compound
Impeller is fixedly connected, and starting motor is connect by clutch with main shaft, and main shaft is mounted in axle sleeve by bearing, rectification bracket and
Annular case component is connected, and annular turbulence-type combustion chamber is located in annular case component, and tail cone is located at the rear portion of composite impeller,
Jet pipe and annular case component are connected to an entirety, clip are equipped on annular case component, for single compound leaf
The gas-turbine unit of wheel is fixed aboard.
The present invention has the advantage that: a kind of rotor of the gas-turbine unit of single composite impeller can effectively simplify knot
Structure mitigates weight, reduces cost, improves rotor machinery rotating property, while can also effectively utilize compressed air stream to turbine leaf
Wheel cools down, to require to create condition to improve turbine inlet temperature or reducing turbine material, is conducive to further
Improve engine performance and service life.
Detailed description of the invention
Fig. 1 is a kind of gas-turbine unit structural schematic diagram of single composite impeller of the present invention.
Fig. 2 is a kind of gas-turbine unit principle schematic diagram of single composite impeller of the present invention.
Fig. 3 is composite impeller structural schematic diagram in a kind of gas-turbine unit of single composite impeller of the present invention.Attached drawing
Description of symbols: 1, start motor 2, clutch 3, main shaft 4, bearing 5, rectification bracket 6, centrifugal compressor blade 7, hollow turbine leaf
Piece 8, annular turbulence-type combustion chamber 9, annular case component 10, tail cone 11, jet pipe I, Cryogenic air II, high temperature air III,
High-temperature fuel gas IV, low temperature combustion gas A, hollow turbine outer tunnel B, hollow turbine vane internal channel C, centrifugal compressor impeller.
Specific embodiment
The preferred embodiment of the present invention is described in detail with reference to the accompanying drawing, so that advantages and features of the invention energy
It is easier to be readily appreciated by one skilled in the art, so as to make a clearer definition of the protection scope of the present invention.
Please refer to shown in Fig. 1,2,3, a kind of gas-turbine unit of single composite impeller, including starting motor (1), from
Clutch (2), main shaft (3), bearing (4), rectification bracket (5), centrifugal compressor blade (6), hollow turbine vane (7), annular rotation
Streaming combustion chamber (8), annular case component (9), tail cone (10), jet pipe (11), the outer rim diameter of centrifugal compressor blade (6)
It is smoothly connected to channel and hollow turbine vane (7) and collectively constitutes one with the compound leaf calmed the anger with expansion work dual function
Wheel, starting motor (1) are connected by clutch (2) with main shaft (3) one end, in the other end and composite impeller of main shaft (3) from
Heart compressor blade (6) is fixedly connected, and outer surface uniformly connects one end of three connecting rods on the right side of starting motor (1), even
The extension bar other end is fixedly connected with rectification bracket (5), and clutch (2), main shaft (3), bearing (4) are located in axle sleeve, main shaft (3)
Both ends are arranged bearing (4), and sleeve outer surface is uniformly provided with three rectification brackets (5), sleeve outer surface and rectification bracket (5) one end
Welding, and rectification bracket (5) other end is fixedly connected with annular case component (9), annular turbulence-type combustion chamber (8) is located at annular
In case component (9), annular case component (9) inner ring is connected with annular turbulence-type combustion chamber (8) inner ring, the annular spiral-flow type
Combustion chamber (8) is held by the peripheral speed of centrifugal compressor blade (6) exit flow in the continuation of insurance of annular turbulence-type combustion chamber (8) relaying
And directly driven hollow turbine vane (7) after combustion heating acceleration, hollow turbine vane (7) rotation drives centrifugal compressor blade
(6) it rotates, annular case component (9) right side is fixedly connected with jet pipe (11), and tail cone (10) is located at centrifugal compressor leaf
Piece (6) rear portion, and it is connected to an entirety with jet pipe (11), the annular case component (9) is equipped with clip, and being used for will
The gas-turbine unit of single composite impeller is fixed on aircraft.
Centrifugal compressor blade (6) and hollow turbine vane (7) are made of one using 3D printing processing technology, are pressed through centrifugation
Compressor wheel (D) compressed Cryogenic air (I) continues centrifugal compressed diffusion by hollow turbine vane internal channel (B), simultaneously
Hollow turbine vane (7) can be cooled down effectively；Starting motor (1) is connected by clutch (2) with main shaft (3), and two
A bearing (4) is used to supports main shaft (3) and is fixedly connected with rectification bracket (5), rectification bracket (5) and annular case component (9)
It is connected, annular swirl combustion chamber (8) is located in case component 9, is existed by the compression high temperature air (II) of turbine hollow passageway (B)
Annular swirl combustion chamber (8) inward eddy burning, high speed, high-temperature fuel gas (III) are expanded by hollow turbine outer tunnel (A) after burning
Acting, driving composite impeller rotation, tail cone (10) are fixed on the tail portion of composite impeller, jet pipe (11) and annular case component
(9) it is connected, makes through the low temperature combustion gas (IV) after hollow turbine vane (7) through jet pipe (10) high speed ejection.
Not limited to this, any change or replacement expected without creative work should all be covered in guarantor of the invention
Within the scope of shield.Therefore, protection scope of the present invention should be determined by the scope of protection defined in the claims.
Claims (3)
1. a kind of gas-turbine unit of single composite impeller, which is characterized in that the outer rim of centrifugal compressor blade (6) is radial
Channel and hollow turbine vane (7), which are smoothly connected, collectively constitutes one with the compound leaf calmed the anger with expansion work dual function
The peripheral speed of centrifugal compressor exit flow is continued to keep simultaneously combustion heating in combustion chamber by wheel, annular swirl combustion chamber (8)
Hollow turbine vane (7) are directly driven after acceleration.
2. a kind of gas-turbine unit of single composite impeller according to claim 1, which is characterized in that single compound
The gas-turbine unit of impeller include starting motor (1), clutch (2), main shaft (3), bearing (4), rectification bracket (5), from
Heart compressor blade (6) and hollow turbine vane (7) be smoothly connected the composite impeller being integrated, annular turbulence-type combustion chamber (8),
Annular case component (9), tail cone (10), jet pipe (11), starting motor (1) pass through clutch (2) and main shaft (3) one end phase
Even, main shaft (3) other end is fixedly connected with the centrifugal compressor blade (6) in composite impeller, and main shaft (3) two sides are arranged bearing
(4), annular turbulence-type combustion chamber (8) is located in annular case component (9), annular case component (9) right side and jet pipe
(11) be fixedly connected, tail cone (10) is located at centrifugal compressor blade (6) rear portion, and with jet pipe (11) be connected to one it is whole
Body.
3. a kind of gas-turbine unit of single composite impeller according to claim 1, which is characterized in that the clutch
Device (2), main shaft (3), bearing (4) are distributed in axle sleeve, and sleeve outer surface is uniformly provided with three rectification brackets (5), axle sleeve appearance
Face and rectification bracket (5) one end are welded, and rectification bracket (5) other end is fixedly connected with annular case component (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810770399.XA CN108952964A (en) | 2018-07-13 | 2018-07-13 | A kind of gas-turbine unit of single composite impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810770399.XA CN108952964A (en) | 2018-07-13 | 2018-07-13 | A kind of gas-turbine unit of single composite impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108952964A true CN108952964A (en) | 2018-12-07 |
Family
ID=64483042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810770399.XA Pending CN108952964A (en) | 2018-07-13 | 2018-07-13 | A kind of gas-turbine unit of single composite impeller |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110242354A (en) * | 2019-05-28 | 2019-09-17 | 华电电力科学研究院有限公司 | The improved efficient radial turbines distribution top pressure power generation system of one kind and its working method |
| CN110273782A (en) * | 2019-07-12 | 2019-09-24 | 南昌航空大学 | A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller |
| CN110318814A (en) * | 2019-07-18 | 2019-10-11 | 北京动力机械研究所 | A kind of closed cycle turbine electricity generation system component test rotor and its manufacturing method |
| CN111336012A (en) * | 2019-11-06 | 2020-06-26 | 西北工业大学 | Centrifugal compressor and turbine blade integrated micro engine impeller disc |
| CN111502779A (en) * | 2020-03-17 | 2020-08-07 | 西北工业大学 | Integrated micro engine impeller disc |
| CN111810243A (en) * | 2020-07-17 | 2020-10-23 | 南昌航空大学 | Compressor-turbine integrated engine |
| CN111894680A (en) * | 2020-06-28 | 2020-11-06 | 南昌航空大学 | Miniature turbojet engine with circulating supercharging composite impeller |
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| EP1209324A2 (en) * | 2000-11-21 | 2002-05-29 | Mitsubishi Heavy Industries, Ltd. | Seal structure for a cooling steam passage in a gas turbine |
| CN101134508A (en) * | 2006-08-31 | 2008-03-05 | 联合工艺公司 | Fan exhaust nozzle for turbofan engine |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110242354A (en) * | 2019-05-28 | 2019-09-17 | 华电电力科学研究院有限公司 | The improved efficient radial turbines distribution top pressure power generation system of one kind and its working method |
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| CN110273782A (en) * | 2019-07-12 | 2019-09-24 | 南昌航空大学 | A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller |
| CN110318814A (en) * | 2019-07-18 | 2019-10-11 | 北京动力机械研究所 | A kind of closed cycle turbine electricity generation system component test rotor and its manufacturing method |
| CN110318814B (en) * | 2019-07-18 | 2022-07-12 | 北京动力机械研究所 | Closed-cycle turbine power generation system component test rotor and manufacturing method thereof |
| CN111336012A (en) * | 2019-11-06 | 2020-06-26 | 西北工业大学 | Centrifugal compressor and turbine blade integrated micro engine impeller disc |
| CN111502779A (en) * | 2020-03-17 | 2020-08-07 | 西北工业大学 | Integrated micro engine impeller disc |
| CN111894680A (en) * | 2020-06-28 | 2020-11-06 | 南昌航空大学 | Miniature turbojet engine with circulating supercharging composite impeller |
| CN111810243A (en) * | 2020-07-17 | 2020-10-23 | 南昌航空大学 | Compressor-turbine integrated engine |
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