CN110332042A - A kind of turbine box structure reducing thermal stress - Google Patents
A kind of turbine box structure reducing thermal stress Download PDFInfo
- Publication number
- CN110332042A CN110332042A CN201910700472.0A CN201910700472A CN110332042A CN 110332042 A CN110332042 A CN 110332042A CN 201910700472 A CN201910700472 A CN 201910700472A CN 110332042 A CN110332042 A CN 110332042A
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- CN
- China
- Prior art keywords
- turbine box
- thermal stress
- aditus laryngis
- turbine
- box structure
- 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
Links
- 230000008646 thermal stress Effects 0.000 title claims abstract description 26
- 239000002912 waste gas Substances 0.000 claims abstract description 6
- 230000009467 reduction Effects 0.000 abstract description 6
- 208000037656 Respiratory Sounds Diseases 0.000 abstract description 4
- 238000005336 cracking Methods 0.000 abstract description 3
- 238000011068 loading method Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000012141 concentrate Substances 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 241000233855 Orchidaceae Species 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Classifications
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- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
-
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Combustion & Propulsion (AREA)
- Theoretical Computer Science (AREA)
- General Chemical & Material Sciences (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Supercharger (AREA)
Abstract
A kind of turbine box structure reducing thermal stress disclosed by the invention, including turbine box enclosure, turbine box inlet flange, engine exhaust air inlet, aditus laryngis, axle sleeve hole, waste gas outlet, bearing body connecting pin, runner, it is characterized in that, using forced structure type at the aditus laryngis.Compared with prior art, the present invention having the following beneficial effects: that 1. reductions concentrate situation because of thermal stress caused by the operating conditions such as temperature loading；2. turbine box aditus laryngis crackle caused by reducing because of thermal stress and the failure risk for extending cracking, improve the fatigue performance of turbine box；3. improving the whole aircraft reliability of booster.
Description
Technical field
The invention belongs to vehicle turbocharger field more particularly to a kind of turbine box structures for reducing thermal stress.
Background technique:
Exhaust-driven turbo-charger exhaust-gas turbo charger is a kind of mechanical device being pressurized using the exhaust energy of engine discharge, it is utilized
Turbine rotation in the exhaust energy driving turbine box of engine, turbine drive coaxial compressor impeller to work, fresh air
Enter compressor through air cleaner, compressor impeller rotary compression fresh air achievees the effect that pressurization.In unit volume
Air capacity increases so that fuel combustion is more abundant, and power improves, fuel consumption rate reduces, while reducing the discharge of tail gas.
Supercharger worm-gear case is directly connected with the exhaust pipe of engine, when work in high temperature, high pressure, run at high speed operating condition,
Working environment very severe, about 650 DEG C -1000 DEG C of exhaust temperature ranges.No with engine start, idling, operation, shutdown etc.
Same operating condition, the working environment of hot and cold alternation transformation, just includes the stream between high-temp waste gas and turbine box among these in addition
Gu it conducts heat to heat, the complicated heat transfer such as solid thermally conductive and fluid structurecoupling boundary Conjugate Heat Transfer between turbine box and bearing body
Process is easy to produce heat and answers so that turbine box is easy to produce thermal stress especially throat site under high-temperature alternate thermal load conditions
Power, thus caused crackle destruction is even more one of most common failure mode of turbine box, so that the reliability of turbine box is affected,
Largely reduce the service life of booster.
Summary of the invention
It is an object of the invention to solve for turbine box because mechanical thermal stress it is high caused by Problem of Failure, especially needle
To due to turbine box operating temperature it is high, and the high-temperature area of fluid operation is just at aditus laryngis, because of temperature distribution is non-uniform generation
Thermal stress causes throat location to be easy to produce crackle, to influence the turbine box knot of the reduction thermal stress of the reliability of booster
Structure.Aditus laryngis cracking failure problem caused by the turbine box structure can be evaded because of thermal stress concentration, improves the whole of turbocharger
Machine reliability.
In order to realize foregoing invention mother, the technical scheme adopted by the invention is that:
It is a kind of reduce thermal stress turbine box structure, including turbine box enclosure, turbine box inlet flange, engine exhaust into
Port, aditus laryngis, axle sleeve hole, waste gas outlet, bearing body connecting pin, runner, which is characterized in that forced structure is used at the aditus laryngis
Form.
In a preferred embodiment of the invention, the top half at the aditus laryngis or lower half portion or whole are adopted
With forced structure type.
The turbine box structure of reduction thermal stress of the invention, the silent place of aditus laryngis take forced Novel structure, based on normal
The turbine box structure of rule, only optimizes turbine box throat location.Using finite element method, to the present invention relates to
Aditus laryngis new structure form turbine box and conventional turbine case carry out the analysis of mechanical thermal stress and compare, whirlpool of the present invention
Roller box aditus laryngis new construction has preferable performance in the numerical value and concentrated position of mechanical thermal stress.
Compared with prior art, the present invention having the following beneficial effects:
1. thermal stress caused by reducing because of operating conditions such as temperature loadings concentrates situation；
2. turbine box aditus laryngis crackle caused by reducing because of thermal stress and the failure risk for extending cracking, improve the resistance to of turbine box
Fatigue behaviour；
3. improving the whole aircraft reliability of booster.
Detailed description of the invention:
The existing turbine box aditus structure schematic sectional view of Fig. 1.
Fig. 2 is the turbine box structure sectional view of the reduction thermal stress of the embodiment of the present invention 1.
Fig. 3 is the turbine box structure sectional view of the reduction thermal stress of the embodiment of the present invention 2.
Fig. 4 is the turbine box structure sectional view of the reduction thermal stress of the embodiment of the present invention 3.
Specific embodiment:
The present invention will be further described for description with reference to the accompanying drawings and examples.
Fig. 1 is the cross-sectional view of existing turbine box.Wherein 11 in Fig. 1 indicate the aditus structure of existing worm gear case.
Embodiment 1
Referring to fig. 2, the turbine box structure shown in figure for reducing thermal stress, including turbine box enclosure 1, turbine box air inlet method
Orchid 2, engine exhaust air inlet 3, aditus laryngis 4, axle sleeve hole 5, waste gas outlet 6, bearing body connecting pin 7, runner 8 etc..Its aditus laryngis 4 is complete
Portion uses forced structure type.
When booster works, engine exhaust enters in runner 8 through engine exhaust air inlet 3, exhaust energy driving dress
The turbine rotor fitted in turbine box is rotated, and high-temp waste gas enters turbine box cavity through runner 8, and turbine box is in alternating hot and cold
Etc. be also easy to produce thermal stress under various workings, and because of the feature of 4 structure of aditus laryngis so that stress position and maximum value are concentrated here,
And the turbine box structure that embodiment is related to, because whirlpool will not be generated when forced structure operates in fluid at aditus laryngis 4 at aditus laryngis 4
Whirlpool, function influence of the temperature loading at aditus laryngis 4 are substantially reduced, so 4 position of aditus laryngis of such structure type is for stress collection
In have and evade effect well, reduce the concentration of stress here, the structural strength of turbine box improved, to booster complete machine
The raising of reliability also has remarkable effect.
Embodiment 2
Referring to Fig. 3, the top half 9 of the turbine box structure shown in figure for reducing thermal stress, aditus laryngis 4 uses forced knot
Configuration formula.Remaining structure of the embodiment is the same as embodiment 1.
Embodiment 3
Referring to fig. 4, the turbine box structure shown in figure for reducing thermal stress, the lower half portion 10 of aditus laryngis 4 is using forced
Structure type.Remaining structure of the embodiment is the same as embodiment 1.
Claims (2)
1. a kind of turbine box structure for reducing thermal stress, including turbine box enclosure, turbine box inlet flange, engine exhaust air inlet
Mouth, aditus laryngis, axle sleeve hole, waste gas outlet, bearing body connecting pin, runner, which is characterized in that forced structure shape is used at the aditus laryngis
Formula.
2. a kind of turbine box structure for reducing thermal stress as described in claim 1, which is characterized in that the upper half at the aditus laryngis
Part or lower half portion or all using forced structure type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910700472.0A CN110332042A (en) | 2019-07-31 | 2019-07-31 | A kind of turbine box structure reducing thermal stress |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910700472.0A CN110332042A (en) | 2019-07-31 | 2019-07-31 | A kind of turbine box structure reducing thermal stress |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110332042A true CN110332042A (en) | 2019-10-15 |
Family
ID=68148221
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910700472.0A Pending CN110332042A (en) | 2019-07-31 | 2019-07-31 | A kind of turbine box structure reducing thermal stress |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110332042A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201071740Y (en) * | 2007-09-05 | 2008-06-11 | 宁波天力增压器有限公司 | Water-cooled turbine box structure of minitype mixed flow turbosupercharger |
| CN103362573A (en) * | 2013-07-25 | 2013-10-23 | 无锡康明斯涡轮增压技术有限公司 | Double-channel volute of turbocharger |
| CN204041222U (en) * | 2014-06-30 | 2014-12-24 | 长城汽车股份有限公司 | Vehicle exhaust turbosupercharger and vehicle |
| CN210738671U (en) * | 2019-07-31 | 2020-06-12 | 湖南天雁机械有限责任公司 | Reduce turbine case structure of thermal stress |
-
2019
- 2019-07-31 CN CN201910700472.0A patent/CN110332042A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201071740Y (en) * | 2007-09-05 | 2008-06-11 | 宁波天力增压器有限公司 | Water-cooled turbine box structure of minitype mixed flow turbosupercharger |
| CN103362573A (en) * | 2013-07-25 | 2013-10-23 | 无锡康明斯涡轮增压技术有限公司 | Double-channel volute of turbocharger |
| CN204041222U (en) * | 2014-06-30 | 2014-12-24 | 长城汽车股份有限公司 | Vehicle exhaust turbosupercharger and vehicle |
| CN210738671U (en) * | 2019-07-31 | 2020-06-12 | 湖南天雁机械有限责任公司 | Reduce turbine case structure of thermal stress |
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