CN104675509B - A kind of turbo-charger sytem design method of high-speed response - Google Patents
A kind of turbo-charger sytem design method of high-speed response Download PDFInfo
- Publication number
- CN104675509B CN104675509B CN201410788326.5A CN201410788326A CN104675509B CN 104675509 B CN104675509 B CN 104675509B CN 201410788326 A CN201410788326 A CN 201410788326A CN 104675509 B CN104675509 B CN 104675509B
- Authority
- CN
- China
- Prior art keywords
- msub
- rotor
- mrow
- inertia
- spiral case
- 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.)
- Active
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a kind of turbo-charger sytem design method of high-speed response, belong to turbo-charger technical field.The present invention is drawn by reducing the rotor-support-foundation system response time according to conservation of energy formula, by reducing the rotary inertia of rotor-support-foundation system, by improving turbine efficiency, by improving compressor efficiency, being realized by reducing mechanical friction dissipated power.The present invention using thin-walled spiral case quality can spiral case more common than same model quality reduction by 50 or so percent；By the flow channel length ratio for adjusting vaned diffuser and vaneless diffuser in combined type diffuser simultaneously, it is possible to achieve compressor flow and pressure ratio are adjusted.
Description
Technical field
The present invention proposes a kind of turbo-charger sytem design method of high-speed response, the sound for reducing turbocharger
Between seasonable, belong to turbo-charger technical field.
Background technology
Turbocharger is the mechanical device for then providing pressurized air for engine by absorbing exhaust energy acting, is
Driving dynamics of the vehicle under different operating modes are met, it is necessary to which to realize that turbo charger speed and engine operating condition change good
Good trackability, namely turbocharger rotor rotating speed realize good trackability with engine exhaust energy.Work as engine throttle
Door aperture increase, what exhaust energy increase increased air capacity, it is necessary to supercharger speed can quickly increase, to meet engine
Need, when engine air throttle aperture reduces, exhaust energy reduce, it is necessary to supercharger speed can rapid decrease, in order to avoid start
Machine admission pressure is too high.Namely need a kind of turbocharger of high-speed response.
The method of traditional reduction turbocharger response time, more from the side for reducing supercharger rotor system rotary inertia
Formula is set about, but influence of the rotor-support-foundation system rotary inertia to the booster response time is very limited.
The content of the invention
In order to solve problems of the prior art, the present invention provides a kind of turbo-charger sytem of high-speed response and set
Meter method.
In turbo-charger sytem, engine exhaust promotes turbine acting, and turbine is driving link, turbine drive rotating shaft and
Compressor is rotated, and compressor is driven member, and compressor compressed air is simultaneously supplied to engine.
The response time of turbocharger is reduced, that is, reduces supercharger rotor system response time, should be main from supercharging
Device rotor-support-foundation system mechanical inertia, three aspect analyzings of thermal inertia and pneumatic inertia.
The mechanical inertia of supercharger rotor system is reduced, can from the mode of lightweight turbine and compressor impeller
Hand, design low inertia turbine and compressor impeller.
The high-temperature gas of engine discharge, turbo blade entrance is reached from volute inlet, promotes turbine rotation acting.Work as hair
When motivation operating mode changes, the gaseous state of engine discharge accordingly changes, i.e., the gaseous state of volute inlet occurs
Change, the now gaseous state change of turbo blade entrance can lag behind the gaseous state change of volute inlet, this gas shape
The hysteresis quality of state change is referred to as pneumatic inertia.
For the whirlpool end of booster, by acting ability of the gas at volute inlet, turbo blade is delivered to rapidly and is entered
, it is necessary to overcome the thermal inertia and pneumatic inertia of spiral case at mouthful.The thermal inertia of spiral case is reduced, thin-walled spiral case can be used, to be reduced
The pneumatic inertia of spiral case, can design spiral case inlet pressure for the log spiral of amendment, the low spiral case for finishing wet number of circular rector such as not.
For the pressure side of booster, compressor impeller is driven member, and when turbine work(changes, supercharger speed is therewith
Positive change, then the discharge state of compressor also change with supercharger speed, blower outlet gaseous state with
The hysteresis quality of supercharger speed change is referred to as the pneumatic inertia of compressor.The pneumatic inertia of compressor is reduced, it is necessary to divide again
Flow field with blower outlet, the length adjustment of the change in blower outlet flow field mainly by streamline after blower outlet.Calm the anger
The short then compressor pneumatic inertia of streamline length is low behind machine outlet, and then compressor pneumatic inertia is high for streamline length.The spy of vaned diffuser
Point is that streamline is short, but the working range of flow and pressure ratio is narrow, is that streamline is long the characteristics of vaneless diffuser, but the work of flow and pressure ratio
Make scope wide.
On the premise of booster flow and pressure ratio working range is ensured, the present invention proposes whirlpool end and pressure side pneumatic inertia
Concept, it is proposed that reduce the method for its response time by reducing booster pneumatic inertia, and derive influence turbine increase
The formula of depressor response time, influences the major parameter of turbocharger response time, to reduce and calm the anger one by one in analytical formula
The pneumatic inertia of machine, present invention employs the combined type diffuser combined by vaned diffuser and vaneless diffuser.
Next the factor of supercharger rotor system response time is influenceed from the angle analysis of energy equation.By the conservation of energy
Understand：
The kinetic energy of rotor-support-foundation system=turbine work(- compressor consumption work(- mechanical friction dissipation work is (1)
The both sides of formula (1) are simultaneously divided by the unit interval can obtain：
Rotor-support-foundation system rotative power=turbine power-compressor consumption power-mechanical Friction dissipation power is (2)
The expression of formula (2) is as follows：
(3) middle I is the rotary inertia of rotor-support-foundation system, ω to formula1For the initial angular velocity of rotor-support-foundation system, ω2For rotor-support-foundation system
Angular speed after the unit interval, θ is the response time of rotor-support-foundation system, PTFor turbine input power, ηTFor turbine efficiency, PC
For compressor power output, ηCFor compressor efficiency, PmFor mechanical friction dissipated power.
(3) formula deformed to can to obtain the expression formula of rotor-support-foundation system response time as follows：
The rotor-support-foundation system response time to be reduced (4) is can be seen that from formula, rotation that can be by reducing rotor-support-foundation system is used to
I is measured to realize, can be by improving turbine efficiency ηTRealize, can be by improving compressor efficiency ηCRealize, reduction can also be passed through
Mechanical friction dissipated power PmRealize.Below for this four parameters are changed, discuss respectively.
Rotary inertia I for reducing rotor-support-foundation system, can be realized by designing low inertia turbine.The present invention proposes one
The design method of kind of low inertia turbine, on the premise of turbine intensity is ensured, the turbine disk per two adjacent roots of blade it
Between carry out loss of weight or duplicate removal processing, that is, remove a part of structure or quality, it is possible to achieve keep turbine it is leaf it is constant in the case of,
Reduce the quality and rotary inertia of the turbine disk.The material that turbine wheel is used is generally high temperature alloy, what compressor impeller was used
Material is generally aluminium alloy, and the density of high temperature alloy is higher than aluminium alloy, so being used using the method ratio of low inertia turbine wheel
The effect of low inertia compressor impeller reduction rotor-support-foundation system rotary inertia is obvious.
For improving turbine efficiency ηT, can be realized by new Volute Design method.
The present invention proposes a kind of design method of new spiral case.The core concept of Volute Design is to ensure each turbine leaf
The gas momentum square of piece porch is equal, i.e., For the mass flow of gas in spiral case, remainder is not
Etc. circular rector, the spiral case inlet pressure designed by this method is the log spiral of an amendment.
Traditional Volute Design method is that premised on gas in spiral case is adiabatic, Volute Design method of the invention considers
The problem of gas is with spiral case heat exchange in spiral case, in order that turbine to gaseous state reacting condition sensitivity in spiral case, it is necessary to snail
Shell try one's best it is few gas in spiral case is exchanged heat, be easy to what gaseous state in the state of turbo blade porch and spiral case changed
Trackability is good.The trackability that gaseous state changes in state and spiral case in order to improve turbo blade porch, it is desirable to reduce
The heat exchange of spiral case and gas in spiral case.By optimizing the complete wet number of spiral case, the overall heat storage capacity of reduction spiral case (needs the body of spiral case
Product is minimized in rational scope), it is that this can be achieved using thin-walled spiral case now on the premise of spiral case pardon is met
One requires.By calculating and verification experimental verification, general, the matter of this thin-walled spiral case more suitable in 1~3mm of wall thickness of thin-walled spiral case
Amount can spiral case more common than same model quality reduction by 50 or so percent.
In addition, there is heat exchange in spiral case between gas and spiral case, gas flowfield in spiral case can be caused to change, it is necessary to same
When Area Compensation is carried out to the section of spiral case.
For improving compressor efficiency ηC, can be realized by designing combined type diffuser.Combined type diffuser is by there is leaf
Diffuser and vaneless diffuser are combined.There are one section of vaneless diffuser, i.e. vaneless diffuser, no leaf in compressor blade exit
Diffuser is followed by being vaned diffuser.By the stream for adjusting vaned diffuser and vaneless diffuser in combined type diffuser
Road length ratio, it is possible to achieve compressor flow and pressure ratio are adjusted simultaneously.
For reduction mechanical friction dissipated power Pm, can be realized by using ball bearing instead of floating bearing, to roll
Dynamic friction replaces sliding friction, reduces mechanical friction dissipated power.But, once bearing is selected, mechanical friction dissipated power Pm
With regard to substantially constant.
In summary, the present invention proposes a kind of turbo-charger sytem design method of high-speed response, it is proposed that whirlpool end
With the concept of pressure side pneumatic inertia, it is proposed that the method for reducing its response time by reducing booster pneumatic inertia, and from
Energy Equation Derived is started with, analyze influence supercharger rotor system response time, that is, the booster response time it is main because
Element, it is proposed that the design method of corresponding reduction rotor-support-foundation system response time.I.e. can be by designing low inertia turbine, to reduce
The rotary inertia I of rotor-support-foundation system；The circular rector such as or not the spiral case inlet pressure for SPL can be designed by new Volute Design method
It is low to finish wet several thin-walled spiral cases, to improve turbine efficiency ηT；Can be combined by vaned diffuser and vaneless diffuser by designing and
Into combined type diffuser, to improve compressor efficiency ηC；Floating bearing can be replaced by using ball bearing, to reduce machine
Tool Friction dissipation power Pm。
The advantage of the invention is that：
1st, the present invention proposes the concept of whirlpool end and pressure side pneumatic inertia, it is proposed that by reduce booster pneumatic inertia come
The method for reducing its response time；
2nd, the present invention is comprehensively analyzed the principal element of influence rotor-support-foundation system response time by energy equation, and is proposed
The method of corresponding reduction rotor-support-foundation system response time；
3rd, the turbo-charger sytem design method of a kind of high-speed response proposed by the present invention, can be in the brand-new supercharging of design
Use, can also be retrofited according to existing booster during device, in the case where rotor-support-foundation system is constant, by designing and changing
Spiral case inlet pressure low finishes wet several thin-walled spiral cases, effectively reduction booster response time for the circular rector such as or not SPL；
4th, the present invention proposes a kind of new Volute Design method, and the thin-walled spiral case designed with this method can effectively drop
The low blower response time, at the same the quality of this thin-walled spiral case can spiral case more common than same model quality reduction by 5 percent
Ten or so；
5th, the present invention proposes a kind of combined type diffuser Design combined by vaned diffuser and vaneless diffuser
Method, by the flow channel length ratio for adjusting vaned diffuser and vaneless diffuser in combined type diffuser, it is possible to achieve calm the anger
Machine flow and pressure ratio are adjusted simultaneously.
Brief description of the drawings
Fig. 1 is low inertia turbine axonometric drawing of the present invention；
Etc. circular rector is not low finishes wet several thin-walled spiral case views for the present invention by Fig. 2A；
Fig. 2 B are the C-C sectional views in Fig. 2A；
Fig. 3 is combined type diffuser view of the present invention；
Fig. 4 is vaned diffuser view of the present invention.
In figure：
1- calms the anger cover；2- locking nuts；3- rotating shafts；4- compressor impellers；
5- vaneless diffusers；6- vaned diffusers.
Embodiment
The present invention is described in detail with reference to the accompanying drawings and examples.
In turbo-charger sytem, engine exhaust promotes turbine acting, and turbine is driving link, drives rotating shaft and calms the anger
Machine is rotated, and compressor is driven member, and compressed air is simultaneously supplied to engine.
The response time of booster is reduced, that is, reduces supercharger rotor system response time, below from energy equation point
The factor of analysis influence supercharger rotor system response time.It was found from the angle of the conservation of energy：
The kinetic energy of rotor-support-foundation system=turbine work(- compressor consumption work(- mechanical friction dissipation work is (1)
The both sides of formula (1) are simultaneously divided by the unit interval can obtain：
Rotor-support-foundation system rotative power=turbine power-compressor consumption power-mechanical Friction dissipation power is (2)
The expression of formula (2) is as follows：
(3) middle I is the rotary inertia of rotor-support-foundation system, ω to formula1For the initial angular velocity of rotor-support-foundation system, ω2For rotor-support-foundation system
Angular speed after the unit interval, θ is the response time of rotor-support-foundation system, PTFor turbine input power, ηTFor turbine efficiency, PC
For compressor power output, ηCFor compressor efficiency, PmFor mechanical friction dissipated power.
(3) formula deformed to can to obtain the expression formula of rotor-support-foundation system response time as follows：
The rotor-support-foundation system response time to be reduced (4) is can be seen that from formula, rotation that can be by reducing rotor-support-foundation system is used to
I is measured to realize, can be by improving turbine efficiency ηTRealize, can be by improving compressor efficiency ηCRealize, reduction can also be passed through
Mechanical friction dissipated power PmRealize.Below for this four parameters are changed, discuss respectively.
Rotary inertia I for reducing rotor-support-foundation system, can be realized by designing low inertia turbine.The present invention proposes one
The design method of kind of low inertia turbine, as shown in figure 1, on the premise of turbine intensity is ensured, adjacent every two on the turbine disk
Remove a part of material between individual root of blade, i.e., duplicate removal is handled, it is possible to achieve keep turbine it is leaf it is constant in the case of, reduce
The quality and rotary inertia of the turbine disk.The material that turbine wheel is used is generally high temperature alloy, the material that compressor impeller is used
Generally aluminium alloy, the density of high temperature alloy is higher than aluminium alloy, so using the method ratio of low inertia turbine wheel using low used
The effect for measuring compressor impeller reduction rotor-support-foundation system rotary inertia is obvious.
For improving turbine efficiency ηT, can be realized by new Volute Design method.Traditional Volute Design method master
There are two kinds：A kind of is based on the circumferential average speed method that speed in spiral case is constant value hypothesis, i.e. Vu=const, by this
The spiral case inlet pressure that method is designed is a spiral of Archimedes；One kind be based on etc. circular rector method or referred to as uniform velocity square
The spiral case that method is designed, i.e. VuR=const, the spiral case inlet pressure designed by this method is a logarithm spiral shell
Spin line.
The present invention proposes a kind of design method of new spiral case.The core concept of Volute Design is to ensure each turbine leaf
The gas momentum square of piece porch is equal, i.e.,Remainder is the circular rector such as not, is designed by this method
Spiral case inlet pressure out is the log spiral of an amendment.Wherein, VuFor gas circumferential speed in spiral case, r is gas in spiral case
The circumferential speed radius of body,For the mass flow of gas in spiral case.
Traditional Volute Design method is that premised on gas in spiral case is adiabatic, Volute Design method of the invention considers
The problem of gas is with spiral case heat exchange in spiral case, in order that turbine to gaseous state change reflection sensitivity in spiral case, it is necessary to snail
Shell try one's best it is few gas in spiral case is exchanged heat, be easy to what gaseous state in the state of turbo blade porch and spiral case changed
Trackability is good.
The trackability that gaseous state changes in state and spiral case in order to improve turbo blade porch, it is desirable to reduce spiral case
With the heat exchange of gas in spiral case.By optimizing the complete wet number (0.01~0.05) of spiral case, the overall heat storage capacity of spiral case is reduced, it is known that
The volume of spiral case is needed to be minimized in rational scope, now on the premise of spiral case pardon is met, using thin-walled snail
Shell is that this requirement can be achieved.Structure as shown in Figure 2 A and 2 B, by calculating and verification experimental verification, the wall thickness of thin-walled spiral case is general
It is more suitable in 1~3mm, the quality of this thin-walled spiral case can spiral case more common than same model quality reduction by 50 percent it is left
It is right.
In addition, there is heat exchange in spiral case between gas and spiral case, gas flowfield in spiral case can be caused to change, it is necessary to same
When Area Compensation is carried out to the section of spiral case.
For improving compressor efficiency ηC, can be realized by designing combined type diffuser.Combined type diffuser is by there is leaf
Diffuser and vaneless diffuser are combined.As shown in figure 3, there is one section of vaneless diffuser at the blade exit of compressor impeller 4, pacify
Vaneless diffuser 5 is filled, vaneless diffuser 5 is followed by being vaned diffuser 6, as shown in Figure 4；Cover 1 of calming the anger has above
Rotating shaft 3 and compressor impeller 4 are fastenedly connected by leaf diffuser 6, locking nut 2.There is leaf expansion in combined type diffuser by adjusting
The flow channel length ratio of depressor and vaneless diffuser, it is possible to achieve compressor flow and pressure ratio are adjusted simultaneously.
For reduction mechanical friction dissipated power Pm, can be realized by using ball bearing instead of floating bearing, to roll
Dynamic friction replaces sliding friction, reduces mechanical friction dissipated power.But, once bearing is selected, mechanical friction dissipated power Pm
With regard to substantially constant.
In summary, the present invention proposes a kind of turbo-charger sytem design method of high-speed response, it is proposed that whirlpool end
With the concept of pressure side pneumatic inertia, it is proposed that the method for reducing its response time by reducing booster pneumatic inertia, and from
Energy Equation Derived is started with, analyze influence supercharger rotor system response time, that is, the booster response time it is main because
Element, it is proposed that the design method of corresponding reduction rotor-support-foundation system response time.I.e. can be by designing low inertia turbine, to reduce
The rotary inertia I of rotor-support-foundation system；The circular rector such as or not the spiral case inlet pressure for SPL can be designed by new Volute Design method
It is low to finish wet several thin-walled spiral cases, to improve turbine efficiency ηT；Can be combined by vaned diffuser and vaneless diffuser by designing and
Into combined type diffuser, to improve compressor efficiency ηC；Floating bearing can be replaced by using ball bearing, to reduce machine
Tool Friction dissipation power Pm。
For one embodiment, the booster that a response time is 15s, the design side provided by the present invention are chosen
Method, response time 0.3s can be reduced using low inertia turbine wheel and compressor impeller, and using the circular rector such as or not low to finish wet number thin
Wall spiral case can reduce response time 7s, using combined type diffuser (the flow channel length ratio of vaneless diffuser and vaned diffuser
Example is 1:2) response time 4s can be reduced, can be reduced response time 0.7s using ball bearing, the response of final booster
Time is reduced to 3s.
Claims (1)
1. a kind of turbo-charger sytem design method of high-speed response, it is characterised in that：According to conservation of energy formula,
The kinetic energy of rotor-support-foundation system=turbine work(- compressor consumption work(- mechanical friction dissipation work is (1)
The both sides of formula (1) are simultaneously divided by the unit interval obtains：
Rotor-support-foundation system rotative power=turbine power-compressor consumption power-mechanical Friction dissipation power is (2)
The expression of formula (2) is as follows：
<mrow>
<mfrac>
<mn>1</mn>
<mn>2</mn>
</mfrac>
<mi>I</mi>
<mrow>
<mo>(</mo>
<msubsup>
<mi>&omega;</mi>
<mn>2</mn>
<mn>2</mn>
</msubsup>
<mo>-</mo>
<msubsup>
<mi>&omega;</mi>
<mn>1</mn>
<mn>2</mn>
</msubsup>
<mo>)</mo>
</mrow>
<mo>/</mo>
<mi>&theta;</mi>
<mo>=</mo>
<msub>
<mi>P</mi>
<mi>T</mi>
</msub>
<msub>
<mi>&eta;</mi>
<mi>T</mi>
</msub>
<mo>-</mo>
<msub>
<mi>P</mi>
<mi>C</mi>
</msub>
<mo>/</mo>
<msub>
<mi>&eta;</mi>
<mi>C</mi>
</msub>
<mo>-</mo>
<msub>
<mi>P</mi>
<mi>m</mi>
</msub>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>3</mn>
<mo>)</mo>
</mrow>
</mrow>
(3) middle I is the rotary inertia of rotor-support-foundation system, ω to formula1For the initial angular velocity of rotor-support-foundation system, ω2Pass through for rotor-support-foundation system
Angular speed after unit interval, θ is the response time of rotor-support-foundation system, PTFor turbine input power, ηTFor turbine efficiency, PCFor pressure
Mechanism of qi power output, ηCFor compressor efficiency, PmFor mechanical friction dissipated power；
(3) formula deformed to can to obtain the expression formula of rotor-support-foundation system response time as follows：
<mrow>
<mi>&theta;</mi>
<mo>=</mo>
<mfrac>
<mrow>
<mfrac>
<mn>1</mn>
<mn>2</mn>
</mfrac>
<mi>I</mi>
<mrow>
<mo>(</mo>
<msubsup>
<mi>&omega;</mi>
<mn>2</mn>
<mn>2</mn>
</msubsup>
<mo>-</mo>
<msubsup>
<mi>&omega;</mi>
<mn>1</mn>
<mn>2</mn>
</msubsup>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<msub>
<mi>P</mi>
<mi>T</mi>
</msub>
<msub>
<mi>&eta;</mi>
<mi>T</mi>
</msub>
<mo>-</mo>
<msub>
<mi>P</mi>
<mi>C</mi>
</msub>
<mo>/</mo>
<msub>
<mi>&eta;</mi>
<mi>C</mi>
</msub>
<mo>-</mo>
<msub>
<mi>P</mi>
<mi>m</mi>
</msub>
</mrow>
</mfrac>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mo>)</mo>
</mrow>
</mrow>
(4) find out from formula, to reduce the rotor-support-foundation system response time, realized by the rotary inertia I for reducing rotor-support-foundation system, it is described
Rotary inertia I include mechanical inertia, thermal inertia and pneumatic inertia；
According to formula (4), the rotor-support-foundation system response time is reduced by way of reducing thermal inertia and pneumatic inertia；
The high-temperature gas of engine discharge, turbo blade entrance is reached from volute inlet, is promoted turbine rotation acting, is worked as engine
When operating mode changes, the gaseous state of engine discharge accordingly changes, i.e. the gaseous state of volute inlet changes,
The now gaseous state change of turbo blade entrance can lag behind the gaseous state change of volute inlet, this gaseous state change
Hysteresis quality be referred to as pneumatic inertia；
For the pressure side of booster, compressor impeller is driven member, and when turbine work(changes, supercharger speed is positive therewith
Change, then the discharge state of compressor also change with supercharger speed, blower outlet gaseous state is with supercharging
The hysteresis quality of device rotation speed change is referred to as the pneumatic inertia of compressor；
For the whirlpool end of booster, by acting ability of the gas at volute inlet, turbo blade porch is delivered to rapidly,
Need to overcome the thermal inertia and pneumatic inertia of spiral case；
The thermal inertia of spiral case is reduced, using thin-walled spiral case, the wall thickness of thin-walled spiral case is 1~3mm；
Reduce the pneumatic inertia of spiral case, design spiral case inlet pressure is the log spiral of amendment, the low snail for finishing wet number of circular rector such as not
Shell,
The pneumatic inertia of compressor is reduced, using the combined type diffusion combined by vaned diffuser and vaneless diffuser
The flow channel length ratio of device, vaneless diffuser and vaned diffuser is 1:2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410788326.5A CN104675509B (en) | 2014-12-17 | 2014-12-17 | A kind of turbo-charger sytem design method of high-speed response |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410788326.5A CN104675509B (en) | 2014-12-17 | 2014-12-17 | A kind of turbo-charger sytem design method of high-speed response |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104675509A CN104675509A (en) | 2015-06-03 |
| CN104675509B true CN104675509B (en) | 2017-11-07 |
Family
ID=53311012
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410788326.5A Active CN104675509B (en) | 2014-12-17 | 2014-12-17 | A kind of turbo-charger sytem design method of high-speed response |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104675509B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201420597Y (en) * | 2009-03-31 | 2010-03-10 | 薛冰 | Ceramic ball bearing turbocharger |
| CN201982168U (en) * | 2011-01-30 | 2011-09-21 | 大连奥托股份有限公司 | Dynamic self-regulation turbocharger |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06129263A (en) * | 1992-10-19 | 1994-05-10 | Nissan Motor Co Ltd | Control of gas turbine engine |
| JP2011043113A (en) * | 2009-08-21 | 2011-03-03 | Mitsubishi Heavy Ind Ltd | Centrifugal pump |
-
2014
- 2014-12-17 CN CN201410788326.5A patent/CN104675509B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201420597Y (en) * | 2009-03-31 | 2010-03-10 | 薛冰 | Ceramic ball bearing turbocharger |
| CN201982168U (en) * | 2011-01-30 | 2011-09-21 | 大连奥托股份有限公司 | Dynamic self-regulation turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104675509A (en) | 2015-06-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7144221B2 (en) | Method and apparatus for assembling gas turbine engines | |
| US9033668B2 (en) | Impeller | |
| EP2378099B1 (en) | Axial turbine wheel | |
| US8453445B2 (en) | Axial turbine with parallel flow compressor | |
| US20100098532A1 (en) | Compressor housing | |
| US20110252790A1 (en) | Axial Turbine | |
| EP2865848B1 (en) | Turbocharger | |
| CN102003410B (en) | High-voltage axial flow fan | |
| CN101985897A (en) | Complex turbine device with variable section | |
| CN107606662A (en) | Novel fan waste gas recycles turbocharging lampblack absorber | |
| CN103195757A (en) | Pneumatic designing method of counter rotating compressor combining pumping of boundary layer | |
| Yang et al. | Experimental research on aerodynamic performance and exit flow field of low pressure axial flow fan with circumferential skewed blades | |
| US20140165559A1 (en) | Multiple scroll axial turbine | |
| Gato et al. | An experimental investigation into the effect of rotor blade sweep on the performance of the variable-pitch Wells turbine | |
| Yu et al. | The experimental researches on improving operating stability of a single stage transonic fan | |
| CN201802444U (en) | Compound turbine device with variable cross-section | |
| CN104675509B (en) | A kind of turbo-charger sytem design method of high-speed response | |
| Wang et al. | Highly-loaded low-reaction boundary layer suction axial flow compressor | |
| CN106870447A (en) | Pipeline compressor special purpose model level | |
| Castegnaro | Effects of NACA 65-blade's trailing edge modifications on the performance of a low-speed tube-axial fan | |
| CN208778047U (en) | Self-priming turbocharger | |
| CN108518348B (en) | Model plane axis stream ducted fan design method | |
| CN107131149A (en) | Impeller | |
| Nguyen et al. | Experimental study of a centrifugal compressor with two successive and counter-rotating impellers | |
| Wang et al. | A study of parameter selection principle and internal flow mechanism in a multi-stage low-reaction axial flow compressor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210615 Address after: No. 1809-03, unit 2, 18 / F, building 2, 87 Jiancai Chengxi Road, Changping District, Beijing 100096 Patentee after: Beijing Keqi future technology development Co.,Ltd. Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220119 Address after: 100080 d4112, 4 / F, block D, Zhizhen building, No. 7, Zhichun Road, Haidian District, Beijing Patentee after: Beijing Lingdong Guochuang Technology Co.,Ltd. Address before: No. 1809-03, unit 2, 18 / F, building 2, 87 Jiancai Chengxi Road, Changping District, Beijing 100096 Patentee before: Beijing Keqi future technology development Co.,Ltd. |
|
| TR01 | Transfer of patent right |