CN109113792A - Recombination boosting turbine - Google Patents
Recombination boosting turbine Download PDFInfo
- Publication number
- CN109113792A CN109113792A CN201811278773.0A CN201811278773A CN109113792A CN 109113792 A CN109113792 A CN 109113792A CN 201811278773 A CN201811278773 A CN 201811278773A CN 109113792 A CN109113792 A CN 109113792A
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- Prior art keywords
- turbine
- order
- level
- duct
- turbo blade
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- 230000006798 recombination Effects 0.000 title claims abstract description 13
- 238000005215 recombination Methods 0.000 title claims abstract description 13
- 230000006978 adaptation Effects 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 13
- 238000002485 combustion reaction Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- 239000000446 fuel Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000002283 diesel fuel Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000003949 liquefied natural gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012067 mathematical method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
Classifications
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
-
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to engine components, particularly relate to a kind of recombination boosting turbine.Including turbine case, the turbine being assemblied on turbine power output shaft, and it is set to turbine surfaces turbo blade；Flywheel is equipped on power output shaft, the first order, second level turbine are symmetrically distributed in flywheel two sides and surface and are equipped with turbo blade, the first, second turbine case is correspondingly provided on the outside of the first order, second level turbine, first, second turbine case is integral by intermediate connecting body connection, whole C-shaped or dome-shaped duct is formed by the outer rim of intermediate connecting body, flywheel, the both ends of duct are connected to the gas circuit port of the first order, second level turbine respectively, and it is concave-shaped arc surface and the rounded mesa structure of upper bottom surface that first order turbine, second level turbine, which are all made of side,.The present invention efficiently solves the technical problems such as acting is discontinuous, energy consumption is high, structure is complicated in the prior art, has many advantages, such as that structure is simple, energy consumption is small, acting is continuous.
Description
Technical field
The invention belongs to engine components, particularly relate to a kind of recombination boosting turbine.
Background technique
Turbogenerator (Turbine engine, or be often simply called Turbine) is that a kind of parts of utilization rotation are worn certainly
It crosses in its fluid and draws the engine type of kinetic energy, belong to one kind of internal combustion engine.It is commonly used for aircraft and large-scale ship or vehicle
Engine.Currently used piston-mode motor, such as two stroke engine, four-stroke engine, also belong to internal combustion engine.In order to
The efficiency for improving work by combustion, generallys use " compressor " or " turbocharger " at present and carrys out the air inflow of greater engine, with
This cooperates more fuel to burn, to achieve the purpose that increase output power.It is reported that being equipped with " turbocharger "
The power increase by 40% of engine can be made even higher, can additionally improve the economy of fuel oil and reduce harmful row of tail gas
Put, from another point of view on say, can also increase substantially the utilization rate of chemical energy.
But common piston-mode motor (such as common four-stroke ic engine) is in the feelings withouyt turbocharger
Delivery temperature under condition is at 600 DEG C or more, and turbine engine exhaust temperature then can reach 1200 DEG C that (this is still having heat dissipation
In the case where measure, illustrate that the thermal efficiency is very low), engine and booster operating temperature after using turbocharger
Can further it increase, this can seriously affect the service life of engine again and shorten normal time between failures, this is mainly
The mechanical strength of some components is caused to reduce after improving due to temperature, along with the change of material and components stress condition
The limit of fatigue strength can be prematurely reached.
Four-stroke ic engine common at present completes working cycles (air-breathing, pressure in the case where rotation two is enclosed
Contracting, outburst, exhaust), actually only have " outburst " this working stage to be only acting state, remaining three working stage is all
Consume energy.
And the gas turbine and jet engine of opposite internal combustion engine, their working condition are only continuous doing work.
But we are also, it is understood that gas turbine and aero-engine are also to be pressurized in the form of turbine drives compressor to realize
Journey, their delivery temperature is higher, therefore aero-engine service life is with regard to shorter (domestic small for more than 2000 under normal circumstances
When, the U.S. is 4000 hours).More seriously, gas turbine and jet engine also have that energy consumption is big, working efficiency
Low, the disadvantages of manufacturing cost is high, structure is increasingly complex.
Turbo blade is the important composition component of turbine section in turbogenerator.High-speed rotating blade is responsible for high temperature height
The air-flow of pressure sucks burner, to maintain the work of engine.Turbine engine blade generally bear biggish working stress and compared with
High operating temperature, and the variation of stress and temperature is also relatively frequently and violent, in addition there are corrosion and wear problems, to work
The requirement of condition is very harsh, therefore it is required that the machining accuracy of blade is very high.It is simultaneously raising turbine efficiency, the table of turbo blade
Face shape is usually designed to the variable cross-section curved surface of distortion, complex-shaped.Thus, the precise geometrical moulding of turbo blade is just at whirlpool
Take turns the prerequisite of processing.Turbo blade geometric modeling, which substantially seeks to find one kind, can effectively meet shape representation and several
What design requirement, and it is convenient for shape information and the mathematical method of product data transform to describe curved surface of turbine vane.Current whirlpool
Turbine type used by wheel engine or gas turbine is all multilayer paddle blade, air-flow be not in flowing it is coherent,
The reflective interaction transmitting really between movable vane piece and stator blade, it is larger that this air turbulence, flow leakage amount just inevitably occurs
The shortcomings that, it causes to transmit compared with atm number and lose.
Applicant retrieval patent document include:
The multifuel engine generallyd use at present, usually existing traditional combustion engine using liquid fuel (such as gasoline,
Diesel oil) on the basis of by increasing control system, increase using gas fuel (such as compressed natural gas, liquefied natural gas), and claim
For dual fuel engine or multifuel engine.Such as multi fuel is disclosed in the patent document of Publication No. CN105697140A
Engine system, the engine are traditional multi-cylinder conventional engine.The patent text of Publication No. CN107849989A
The equipment for multifuel engine is disclosed in offering, the engine belongs to multi-cylinder conventional engine.No matter adopting
With which kind of fuel, it cannot get rid of that the acting of conventional reciprocating internal-combustion piston engine is discontinuous, energy consumption is high, knot in structure and performance
The disadvantages of structure is complicated.
Summary of the invention
The purpose of the present invention is to provide one kind can be effectively reduced energy consumption, acting compared with prior art continuously and structure letter
Single recombination boosting turbine.
Overall technology design of the invention is:
Recombination boosting turbine, including turbine case, the turbine being assemblied on turbine power output shaft, and it is set to turbine
Surface turbines blade；Flywheel is equipped on power output shaft, first order turbine and second level turbine are symmetrically distributed in flywheel two
Side and surface are equipped with turbo blade, are correspondingly provided with the first turbine case and the second turbine on the outside of first order turbine, second level turbine
Shell, the first turbine case are connect by intermediate connecting body with the second turbine case and are integral, by the outer rim shape of intermediate connecting body, flywheel
Integral C-shaped or dome-shaped duct, the both ends of duct connect with the gas circuit port of first order turbine and second level turbine respectively
Logical, it is concave-shaped arc surface and the rounded mesa structure of upper bottom surface that first order turbine, second level turbine, which are all made of side,.
Particular technique of the invention is conceived also:
Turbo blade in the present invention preferably adopts the following technical scheme that, turbo blade is in scroll, and turbo blade is the
First turbine and second level turbine surfaces are radially distributed.
To realize equilibrium of the gas to turbo blade impetus power in duct, preferred technical solution is that duct is in
Between connect in intracoelomic cavity radially in angularly uniformly distributed.
To realize that it is smooth that air-flow conveys in first order turbine, duct, second level turbine, preferred technical solution is,
The air stream outlet of first order turbine and the air flow inlet of second level turbine and the duct both ends on adjacent intermediate connecting body
Opening direction adaptation.More preferably technical solution is that the air stream outlet of first order turbine and the gas of second level turbine flow into
The opening direction at the tangential direction of mouth and the duct both ends on adjacent intermediate connecting body is in the same direction or substantially in the same direction, and air-flow is flowed through
Duct or structural body surface be smooth surface blending.
Applicant it should be understood that
In the description of the present invention, term " surface ", " two sides ", " outer rim ", " side ", " radial direction ", " both ends ", " middle part "
The orientation or positional relationship of equal instructions is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of simplifying this hair of description
It is bright, rather than the device or element of indication or suggestion meaning must have a particular orientation, be constructed and operated in a specific orientation,
Therefore it is not considered as limiting the invention.In addition, term " first ", " second " are used for description purposes only, and cannot understand
For indication or suggestion relative importance.
The significant technological progress of the substantive distinguishing features of the invention having and acquirement is:
1, air-flow is rotated in turbo blade and is centrifuged in the channel that first order turbine and turbo blade are formed in flow process
Can be along turbo blade toward tip motions to duct under the action of power, gas exports after turning in duct from the duct other end
Spray and impact the turbo blade of second level turbine, drive power output shaft acting, to realize recombination boosting effect, sufficiently into
The conversion of row energy improves turbine efficiency and reduces energy consumption.
2, by first, second grade of turbine, the turbine main body of turbine case, intermediate connecting body and flywheel composition, can
Under the premise of realizing recombination boosting, due to the effect of flywheel, there is preferable energy reserve effect, first, second grade of turbo-side
The concave cambered surface in face and the rounded mesa structure of upper bottom surface have preferable heat dissipation effect while saving making material
Fruit.
3, air-flow is close to the main effect face of blade when impacting blade, and there is very high air-flow to depend on characteristic and conversion effect
Rate is compared more existing paddle blade (rotor and stator blade), is not in air turbulence phenomenon, leakage rate is relatively small, turbo blade
It is distributed and radially extends in the concave-shaped arc surface of turbine, turbo blade stress condition is greatly improved compared to paddle blade, can be compared with
Cavitation is avoided well, significantly improves engine life.
Detailed description of the invention
Fig. 1 is overall structure diagram of the invention.
Cutting plane is C-C direction view in Fig. 3 in Fig. 1.
Fig. 2 is the left view of Fig. 1.
Fig. 3 is the D-D direction view of Fig. 1.
Fig. 4 is the structural schematic diagram of turbine and turbo blade.
The main view of Fig. 4 A turbine and turbo blade.
Fig. 4 B is the G-G direction view of Fig. 4 A.
Fig. 4 C is the rearview of Fig. 4 A.
Fig. 5 is distributed architecture schematic diagram of the duct in the right side of intermediate connecting body.
Distribution main view of Fig. 5 A duct in the right side of intermediate connecting body.
Fig. 5 B is the F-F direction view of Fig. 5 A.
Fig. 5 C is the rearview of Fig. 5 A.
Appended drawing reference in attached drawing is as follows:
1, power output shaft；2, flywheel；3, turbo blade；4, first order turbine；5, second level turbine；6, the first turbine
Shell；7, the second turbine case；8, intermediate connecting body；9, duct.
Specific embodiment
The present invention is described further with reference to embodiments, but should not be construed as limitation of the invention, the present invention
Protection scope be subject to the content of claim record, any equivalent technical elements replacement made according to specification,
Protection scope of the present invention is not departed from.
The overall structure of the present embodiment is as shown, including turbine case, is assemblied in the whirlpool on turbine power output shaft 1
Wheel, and it is set to turbine surfaces turbo blade 3；Flywheel 2, first order turbine 4 and the second level are equipped on power output shaft 1
Turbine 5 is symmetrically distributed in 2 two sides of flywheel and surface is equipped with turbo blade 3, and correspondence is set on the outside of first order turbine 4, second level turbine 5
There are the first turbine case 6 and the second turbine case 7, the first turbine case 6 and the second turbine case 7 pass through intermediate connecting body 8 and be connected as one
It is whole, whole C-shaped or dome-shaped duct 9 is formed by the outer rim of intermediate connecting body 8, flywheel 2, the both ends of duct 9 respectively with
The connection of the gas circuit port of first order turbine 4 and second level turbine 5, it is recessed that first order turbine 4, second level turbine 5, which are all made of side,
Shape cambered surface and the rounded mesa structure of upper bottom surface.
Turbo blade 3 is in scroll, and turbo blade 3 radially divides in first order turbine 4 and 5 surface of second level turbine
Cloth.
Duct 9 is angularly uniformly distributed in a ring in 8 inner cavity of intermediate connecting body.
On the air stream outlet of first order turbine 4 and the air flow inlet of second level turbine 5 and adjacent intermediate connecting body 8
The opening direction at 9 both ends of duct is adapted to.
More preferably technical solution is, the air flow inlet of the air stream outlet and second level turbine 5 of first order turbine 4
The opening direction at 9 both ends of duct in tangential direction and adjacent intermediate connecting body 8 is in the same direction or substantially in the same direction, what air-flow was flowed through
Duct or structural body surface are smooth surface blending.
The working principle of the present embodiment is:
Enter and push the turbo blade being distributed thereon by the entrance of gas from the first order turbine 4 of combustion chamber output,
Turbo blade 3 can be along turbo blade 3 toward tip motions to duct 9 under the action of rotating centrifugal force, and gas occurs to turn in duct 9
The turbo blade 3 for spraying and impacting second level turbine 5, first order turbine 4, second level turbine are exported from 9 other end of duct backward
Turbo blade 3 in shell 5 does work, and by 1 output torque of power transmission shaft, to realize recombination boosting effect.
Claims (4)
1. recombination boosting turbine, including turbine case, the turbine being assemblied on turbine power output shaft (1), and it is set to whirlpool
Wheel surface turbo blade (3)；It is characterized in that being equipped with flywheel (2) on the power output shaft (1), first order turbine (4)
And second level turbine (5) is symmetrically distributed in flywheel (2) two sides and surface and is equipped with turbo blade (3), first order turbine (4), the
The first turbine case (6) and the second turbine case (7), the first turbine case (6) and the second turbine are correspondingly provided on the outside of two-stage turbine (5)
Shell (7) is integral by intermediate connecting body (8) connection, is formed by the outer rim of intermediate connecting body (8), flywheel (2) whole C-shaped
Or the duct (9) of dome-shaped, the both ends of duct (9) connect with the gas circuit port of first order turbine (4) and second level turbine (5) respectively
Logical, it is concave-shaped arc surface and the rounded mesa structure of upper bottom surface that first order turbine (4), second level turbine (5), which are all made of side,.
2. recombination boosting turbine according to claim 1, it is characterised in that turbo blade (3) is in scroll, turbo blade
(3) radially distributed in first order turbine (4) and second level turbine (5) surface.
3. recombination boosting turbine according to claim 1, it is characterised in that duct (9) is in intermediate connecting body (8) inner cavity
In radially angularly uniformly distributed.
4. recombination boosting turbine according to any one of claim 1-3, it is characterised in that the air-flow of first order turbine (4)
The opening direction of the air flow inlet and duct (9) both ends on adjacent intermediate connecting body (8) of outlet and second level turbine (5)
Adaptation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811278773.0A CN109113792A (en) | 2018-10-30 | 2018-10-30 | Recombination boosting turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811278773.0A CN109113792A (en) | 2018-10-30 | 2018-10-30 | Recombination boosting turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109113792A true CN109113792A (en) | 2019-01-01 |
Family
ID=64855611
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811278773.0A Pending CN109113792A (en) | 2018-10-30 | 2018-10-30 | Recombination boosting turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109113792A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112483190A (en) * | 2020-11-27 | 2021-03-12 | 日照黎阳工业装备有限公司 | Turbine blade based on aeroengine possesses vortex structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1536166A (en) * | 1975-04-14 | 1978-12-20 | Phillips Petroleum Co | Combustors |
| US20040219079A1 (en) * | 2003-01-22 | 2004-11-04 | Hagen David L | Trifluid reactor |
| CN102536432A (en) * | 2012-02-13 | 2012-07-04 | 清华大学 | Counter-rotating turbine combination device and engine system with same |
| CN102619616A (en) * | 2011-01-30 | 2012-08-01 | 梁天宇 | Turbine supercharger |
| US20170175564A1 (en) * | 2015-12-16 | 2017-06-22 | Daniel Schlak | Flywheel with Inner Turbine, Intermediate Compressor, and Outer Array of Magnets |
| CN107923309A (en) * | 2015-06-16 | 2018-04-17 | 普拉特 - 惠特尼加拿大公司 | Compound cycle engine |
| CN208966373U (en) * | 2018-10-30 | 2019-06-11 | 常胜 | Recombination boosting turbine |
-
2018
- 2018-10-30 CN CN201811278773.0A patent/CN109113792A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1536166A (en) * | 1975-04-14 | 1978-12-20 | Phillips Petroleum Co | Combustors |
| US20040219079A1 (en) * | 2003-01-22 | 2004-11-04 | Hagen David L | Trifluid reactor |
| CN102619616A (en) * | 2011-01-30 | 2012-08-01 | 梁天宇 | Turbine supercharger |
| CN102536432A (en) * | 2012-02-13 | 2012-07-04 | 清华大学 | Counter-rotating turbine combination device and engine system with same |
| CN107923309A (en) * | 2015-06-16 | 2018-04-17 | 普拉特 - 惠特尼加拿大公司 | Compound cycle engine |
| US20170175564A1 (en) * | 2015-12-16 | 2017-06-22 | Daniel Schlak | Flywheel with Inner Turbine, Intermediate Compressor, and Outer Array of Magnets |
| CN208966373U (en) * | 2018-10-30 | 2019-06-11 | 常胜 | Recombination boosting turbine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112483190A (en) * | 2020-11-27 | 2021-03-12 | 日照黎阳工业装备有限公司 | Turbine blade based on aeroengine possesses vortex structure |
| CN112483190B (en) * | 2020-11-27 | 2022-05-13 | 日照黎阳工业装备有限公司 | Turbine blade based on aeroengine possesses vortex structure |
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| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Chang Sheng Inventor after: Lin Jinguo Inventor after: Jiang Shaoqing Inventor after: Liu Yinchang Inventor after: He Wei Inventor before: Chang Sheng Inventor before: Lin Jinguo Inventor before: Wang Keyin Inventor before: Jiang Shaoqing Inventor before: Liu Yinchang Inventor before: He Wei |