CN110080830A - A kind of radial-flow type supercharging device of included back disk impinging cooling - Google Patents
A kind of radial-flow type supercharging device of included back disk impinging cooling Download PDFInfo
- Publication number
- CN110080830A CN110080830A CN201910375903.0A CN201910375903A CN110080830A CN 110080830 A CN110080830 A CN 110080830A CN 201910375903 A CN201910375903 A CN 201910375903A CN 110080830 A CN110080830 A CN 110080830A
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- Prior art keywords
- turbine
- compressor
- radial
- cooling
- gas
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- 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.)
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- 238000001816 cooling Methods 0.000 title claims abstract description 52
- 239000007789 gas Substances 0.000 claims abstract description 20
- 239000000112 cooling gas Substances 0.000 claims abstract description 17
- 229910003460 diamond Inorganic materials 0.000 claims description 3
- 239000010432 diamond Substances 0.000 claims description 3
- 238000009827 uniform distribution Methods 0.000 claims description 3
- 238000005507 spraying Methods 0.000 abstract 1
- 239000002826 coolant Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a kind of radial-flow type supercharging devices of included back disk impinging cooling, including, turbine, intermediate and the compressor set gradually along axial direction, turbine and compressor are fixed on intermediate two sides；It is equipped with annular cooling chamber in intermediate, is equipped with turbine wheel shaft in intermediate, turbine wheel shaft one end is equipped with turbine, and the other end is equipped with compressor impeller；Cooling gas, which is equipped with, between compressor outlet volute and annular cooling chamber introduces pipe, annular cooling chamber is equipped with jet hole towards the side of turbine, cooling gas introduces pipe and can introduce the gas in compressor outlet volute in annular cooling chamber, and is ejected on the turbine by jet hole.The device can introduce pipe in the spraying high-pressure gas to turbine at compressor outlet volute by cooling gas, cool down to turbine, improve the working environment of turbine, improve service life.
Description
Technical field
The present invention relates to turbines and technical field of internal combustion engines, and in particular to the radial-flow type pressurization of included back disk impinging cooling
Device.
Background technique
Microminiature gas turbine has that small in size, light-weight, noise is small, the series of advantages such as at low cost, thus answers extensively
In aviation, distributed energy, petroleum, railway and shipbuilding industry, the thermal efficiency of cycle of gas turbine is with turbine inlet temperature
Degree rises and is continuously improved, therefore in order to improve the efficiency of gas turbine, usually increase turbine-entry temperature.However turbine inlet
The promotion of temperature is limited by the resistance to mild reliability of material under turbine rotor high temperature thermal load conditions again.
In large-scale gas turbine, generally for turbo blade, hollow structure design is generallyd use, by turbine
Blade interior is led to cooling air and is cooled down to it, and then promotes the heat resistance of turbine.And in microminiature gas turbine due to
The limitation of size and cost, usually using radial-flow turbine.In order to promote pneumatic efficiency, Radial-flow Turbine Vanes are generallyd use
Three-dimensional bending designs, and thinner thickness, is difficult to use it type of cooling of axial flow turbine to carry out to lead to cold air in actual use
Inside is cooling.Therefore how microminiature gas turbine radial-flow turbine is effectively cooled down, promotes its heat resistance, from
And its whirlpool end inlet temperature can be increased, and then promote its complete machine thermal efficiency, it is microminiature gas turbine design all the time
One difficult point.
Another technical background is, with the continuous promotion of engine conditions, turbocharger radial turbine inlet temperature
It is obviously increased with revolving speed, the increase of thermic load reduces the mechanical property of radial turbine rotor material, and the increase of revolving speed is again
Increase the centrifugal stress of radial turbine rotor, thus the turbine rotor of turbocharger under by high operating condition high heat load influenced
When reliability also face huge challenge.
Lead to overcooled mode to cool down turbocharger turbine rotor, reduces the temperature of its rotor material, at
For a kind of solution of low cost of the high operating condition turbine rotor reliability of improvement.
Two above application background all refers to the cooling problem of radial turbine machine rotor, therefore how to radial-flow type
Turbine rotor effectively cool down, and is the current technical issues that need to address of those skilled in the art.
Summary of the invention
The invention proposes a kind of radial-flow type supercharging device of included back disk impinging cooling, which can will calm the anger
Gas at machine outlet volute is introduced at turbine, for cooling down to turbine, be ensure that and is increased working long hours for device.
The technological means that the present invention uses is as follows:
A kind of radial-flow type supercharging device of included back disk impinging cooling, including, the turbine that is set gradually along axial direction, centre
Body and compressor, the turbine and compressor are fixed on the intermediate two sides；The turbine includes turbine inlet
Volute, turbine air inlet housing and turbine；The compressor includes compressor impeller, compressor diffuser, compressor air inlet machine pipe
And compressor outlet volute；It is equipped with annular cooling chamber and bearing chamber in the intermediate, is arranged in the bearing bore room
There is turbine wheel shaft, described turbine wheel shaft one end is equipped with the turbine, and the turbine wheel shaft other end is equipped with the compressor impeller；Institute
It states and is equipped with cooling gas introducing pipe between compressor outlet volute and the annular cooling chamber, annular cooling chamber direction
The side of turbine is equipped with jet hole, and the cooling gas introduces pipe can will be described in the gas in the compressor outlet volute introduces
In annular cooling chamber, and it is ejected on the turbine by the jet hole.
Further, the cooling gas, which is introduced into pipe, is additionally provided with valve, and the valve is with pneumatically or electrically executing
The valve of device.
Further, the turbine is radial-flow turbine.
Further, it is 2-20 that the jet hole, which is quantity, the axis direction of the jet hole and the axis of turbine wheel shaft
Less than 45 °, the shape of the jet hole is circle, rectangle, triangle or diamond shape for angular separation.
Further, the axis direction of the jet hole and the axis direction of turbine wheel shaft are parallel, and the jet hole is described
Side circumference uniform distribution of the annular cooling chamber towards turbine.
Compared with the prior art, the radial-flow type supercharging device of included back disk impinging cooling of the present invention has with following
Beneficial effect: pipe is introduced by being equipped with cooling gas between compressor outlet volute and intermediate, can be realized the small portion that introduces
The pressure-air of mechanism of qi is divided, and is cooled down by annular cooling chamber to turbine, cooled external air supply system is saved
System.The radial-flow type supercharging device structure of this included back disk impinging cooling is simple, and production easy to process is at low cost.Carry on the back disk jet stream
In the intermediate of supercharging device, structure is more compact, occupies little space for orifice plate and annular cooling chamber's design.
Detailed description of the invention
Fig. 1 is the structure chart of the radial-flow type supercharging device of included back disk impinging cooling disclosed by the invention；
Fig. 2 is the structure sectional view of the radial-flow type supercharging device of included back disk impinging cooling disclosed by the invention；
Fig. 3 is the axial partial sectional view of Fig. 2；
Fig. 4 is the structure chart that cooling gas introduces pipe；
Fig. 5 is the structure chart of intermediate；
Fig. 6 is view of the intermediate from turbine side, is only shown in figure towards the one side of turbine and setting at it
On jet hole.
In figure: 1, compressor outlet volute, 2, valve, 3, cooling gas introducing pipe, 4, compressor impeller, 5, compressor expansion
Depressor, 6, intermediate, 7, cooling pipe outlet, 8, turbine air inlet housing, 9, turbine inlet volute, 10, back dish gap, 11,
Turbine, 12, turbine, 13, turbine chassis, 14, back disk jet stream orifice plate, 15, jet hole, 16, annular cooling chamber, 17, calm the anger
Machine, 18, compressor air inlet machine pipe, 19, turbine wheel shaft, 20, annular coolant flow channel, 21, bearing block, 22, bearing chamber.
Specific embodiment
It is as shown in Figure 1, Figure 2 and Figure 3 the radial-flow type supercharging device of included back disk impinging cooling disclosed by the invention, packet
It includes, turbine 12, intermediate 6 and the compressor 17 set gradually along axial direction, the turbine 12 and compressor 17 are fixed on
6 two sides of intermediate；The turbine 12 includes turbine inlet volute 9, turbine air inlet housing 8 and turbine 11；It is described
Compressor 17 includes compressor impeller 4, compressor diffuser 5, compressor air inlet machine pipe 18 and compressor outlet volute 1；It is preferred that
Ground, the turbine 12 use radial-flow turbine.
6 one end of intermediate is fixedly connected with turbine inlet volute 9, and the other end is fixedly connected with compressor diffuser 5, in
Mesosome 6 can be fixedly connected with turbine 12 and compressor 17 by flange or yoke configurations.
As shown in figure 5, being equipped with annular cooling chamber 16 and bearing chamber 22, the bearing chamber 22 in the intermediate 6
It is placed in intermediate centre, bearing block 21 is equipped in the bearing chamber 22, turbine wheel shaft 19 is installed in bearing block 21, it is described
One end that turbine wheel shaft 19 is in turbine 12 is equipped with the turbine 11, and turbine 11 is in turbine inlet volute 9, the whirlpool
One end that wheel shaft 19 is in compressor 17 is equipped with the compressor impeller 4, in the present embodiment, 19 one end of turbine wheel shaft and turbine
11 welding, the other end are tightened compressor impeller by nut.When assembly, turbine will be welded with and be installed with the turbine wheel shaft of bearing and worn
Enter bearing chamber, and bearing is located on bearing block, then the other end penetrates compressor impeller, then with nut by gas compressor blade
Wheel is tightened on turbine wheel shaft.The compressor impeller 4 is in compressor diffuser 5；The compressor outlet volute 1 with it is described
It is equipped with cooling gas between annular cooling chamber 16 and introduces pipe 3, cooling gas, which introduces pipe 3, can be hose or rigid pipe, cooling
3 one end of gas inlet tube is equipped with cooling pipe outlet 7, the annular coolant flow channel that cooling pipe outlet is formed with annular cooling chamber
20 connections, as shown in Figure 5 and Figure 6, the annular cooling chamber 16 are equipped with jet hole 15 towards the side of turbine 11, specifically,
Intermediate towards the side of turbine be equipped with back disk jet stream orifice plate 14, back disk jet stream orifice plate and intermediate can be separate structure or
Integral structure when carrying on the back disk jet stream orifice plate and intermediate when separate structure, can be fixed on by bolt by disk jet hole version is carried on the back
Intermediate is towards the side of turbine, and in the present embodiment, back disk jet stream orifice plate is integrally cast with intermediate, in back disk jet stream
Multiple jet holes 15 are provided on orifice plate 14, jet hole 15 is connected to annular coolant flow channel 20, and the cooling gas introduces pipe 3 can
High pressure gas in the compressor outlet volute 1 is introduced in the annular cooling chamber 16, after annular coolant flow channel
It is ejected by the jet hole 15 on the turbine chassis 13 of the turbine 11.
The specific work process of the radial-flow type supercharging device of included back disk impinging cooling disclosed by the invention is as follows: turbine
Air inlet volute connected with engine whirlpool front exhaust pipe, turbine air inlet housing is connect with engine whirlpool heel row tracheae, compressor into
Tracheae is connect with engine charge filtering pipeline, and compressor air inlet housing is connect with engine intake manifold or intercooler pipe, hair
Gas after motivation burning enters turbine runner by turbine inlet volute and pushes turbine rotation, and turbine is in burning gases
Push lower rotation acting, and compressor impeller rotation acting driven by turbine wheel shaft, compressor impeller rotation so that air from pressure
Mechanism of qi air inlet pipe enters in compressor, high-speed rotating compressor impeller effect under, air from compressor impeller center get rid of to
Compressor impeller outer rim, pressure are gradually increased, and speed reduces after entering compressor diffuser by the air that compressor impeller flows out,
Pressure improves again, finally enters engine intake manifold or intercooler pipe by compressor outlet volute outflow compressor, leads to
The pressure-air a part for crossing compressor outlet volute introduces pipe by cooling gas and enters intermediate intracorporal annular cooling chamber,
Cooling gas is ejected on the turbine chassis of turbine after annular coolant flow channel by jet hole, the gas for cooling down to turbine
Body pass through back dish gap of the turbine between turbine inlet volute after with promotion turbine rotation burning after gas together with from
The discharge of turbine air inlet housing.
Further, as shown in figure 4, the cooling gas, which is introduced into pipe, is additionally provided with valve 2, it is preferable that valve be with
The pneumatically or electrically valve of actuator, the valve can be according to the operating conditions of supercharging device, according to the control strategy demarcated, certainly
The opening and closing of dynamic control valve.
Further, it is 2-20 that the jet hole, which is quantity, the axis direction of the jet hole and the axis of turbine wheel shaft
Less than 45 °, the shape of the jet hole is circle, rectangle, triangle or diamond shape, in the present embodiment, jet hole for angular separation
Shape be round hole.
Further, the axis direction of the jet hole and the axis direction of turbine wheel shaft are parallel, and the jet hole is described
Side circumference uniform distribution of the annular cooling chamber towards turbine.
It should be noted that herein axial, circumferential direction, radial direction are on the basis of turbine wheel shaft, the extending direction of turbine wheel shaft is
For axial direction, in the present embodiment, turbine inlet volute and turbine air inlet housing can be and be integrally cast, and be also possible to lead to
Cross design flange or clamp connection.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (5)
1. a kind of radial-flow type supercharging device of included back disk impinging cooling, it is characterised in that: including along the whirlpool that axial direction is set gradually
Turbine, intermediate and compressor, the turbine and compressor are fixed on the intermediate two sides；
The turbine includes turbine inlet volute, turbine air inlet housing and turbine；
The compressor includes compressor impeller, compressor diffuser, compressor air inlet machine pipe and compressor outlet volute；
It is equipped with annular cooling chamber and bearing chamber in the intermediate, is provided with turbine wheel shaft, the whirlpool in the bearing bore room
Wheel shaft one end is equipped with the turbine, and the turbine wheel shaft other end is equipped with the compressor impeller；
It is equipped with cooling gas between the compressor outlet volute and the annular cooling chamber and introduces pipe, the annular cooling chamber
Room is equipped with jet hole towards the side of turbine, and the cooling gas, which introduces pipe, to draw the gas in the compressor outlet volute
Enter in the annular cooling chamber, and is ejected on the turbine by the jet hole.
2. the radial-flow type supercharging device of included back disk impinging cooling according to claim 1, it is characterised in that: the cooling
Valve is additionally provided in gas inlet tube, the valve is the valve with pneumatically or electrically actuator.
3. the radial-flow type supercharging device of included back disk impinging cooling according to claim 1 or 2, it is characterised in that: described
Turbine is radial-flow turbine.
4. the radial-flow type supercharging device of included back disk impinging cooling according to claim 1, it is characterised in that: the jet stream
Hole is that quantity is 2-20, and the axis direction of the jet hole and the axis direction angle of turbine wheel shaft are less than 45 °, the jet hole
Shape be circle, rectangle, triangle or diamond shape.
5. the radial-flow type supercharging device of included back disk impinging cooling according to claim 4, it is characterised in that: the jet stream
The axis direction in hole and the axis direction of turbine wheel shaft are parallel, and the jet hole is in the annular cooling chamber towards the side of turbine
Circumference uniform distribution.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910375903.0A CN110080830A (en) | 2019-05-07 | 2019-05-07 | A kind of radial-flow type supercharging device of included back disk impinging cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910375903.0A CN110080830A (en) | 2019-05-07 | 2019-05-07 | A kind of radial-flow type supercharging device of included back disk impinging cooling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110080830A true CN110080830A (en) | 2019-08-02 |
Family
ID=67419078
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910375903.0A Withdrawn CN110080830A (en) | 2019-05-07 | 2019-05-07 | A kind of radial-flow type supercharging device of included back disk impinging cooling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110080830A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217193A (en) * | 2021-05-14 | 2021-08-06 | 西北工业大学 | Turbine wheel disc water spray cooling structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE849038C (en) * | 1942-05-23 | 1952-09-11 | Alfred Dr-Ing Buechi | Gas turbine |
| GB1175737A (en) * | 1967-04-21 | 1969-12-23 | Napier & Son Ltd | Improvements in Internal Combustion Engine Superchargers |
| US4376617A (en) * | 1980-04-17 | 1983-03-15 | Toyota Jidosha Kogyo Kabushiki Kaisha | Turbocharger for use in an internal combustion engine |
| EP1577520A2 (en) * | 2004-03-17 | 2005-09-21 | Wärtsilä Finland Oy | Turbo compressor arrangement for piston engines |
| CN104213974A (en) * | 2013-05-31 | 2014-12-17 | 通用汽车环球科技运作有限责任公司 | Turbocharger assembly |
-
2019
- 2019-05-07 CN CN201910375903.0A patent/CN110080830A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE849038C (en) * | 1942-05-23 | 1952-09-11 | Alfred Dr-Ing Buechi | Gas turbine |
| GB1175737A (en) * | 1967-04-21 | 1969-12-23 | Napier & Son Ltd | Improvements in Internal Combustion Engine Superchargers |
| US4376617A (en) * | 1980-04-17 | 1983-03-15 | Toyota Jidosha Kogyo Kabushiki Kaisha | Turbocharger for use in an internal combustion engine |
| EP1577520A2 (en) * | 2004-03-17 | 2005-09-21 | Wärtsilä Finland Oy | Turbo compressor arrangement for piston engines |
| CN104213974A (en) * | 2013-05-31 | 2014-12-17 | 通用汽车环球科技运作有限责任公司 | Turbocharger assembly |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217193A (en) * | 2021-05-14 | 2021-08-06 | 西北工业大学 | Turbine wheel disc water spray cooling structure |
| CN113217193B (en) * | 2021-05-14 | 2022-05-27 | 西北工业大学 | Turbine wheel disc water spray cooling structure |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20190802 |