CN107762955A - The testing stand and test method that eddy flow influences on axial flow compressor aerodynamic stability - Google Patents
The testing stand and test method that eddy flow influences on axial flow compressor aerodynamic stability Download PDFInfo
- Publication number
- CN107762955A CN107762955A CN201710809873.0A CN201710809873A CN107762955A CN 107762955 A CN107762955 A CN 107762955A CN 201710809873 A CN201710809873 A CN 201710809873A CN 107762955 A CN107762955 A CN 107762955A
- Authority
- CN
- China
- Prior art keywords
- compressor
- axial flow
- axial
- flow
- admission line
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
Abstract
The testing stand and test method influenceed the invention discloses a kind of eddy flow on axial flow compressor aerodynamic stability, including rotational flow generator, admission line, radome fairing, axial flow compressor, discharge duct, choke valve and the first motor set gradually；By adjusting the anglec of rotation of two adjustable plates in rotational flow generator, realize single whirlpool in the same direction in admission line, reversely single whirlpool, to whirlpool these three typical cyclone structures switching；The rotating speed of centrifugal compressor is controlled by the second motor, realizes the strength control of admission line inward eddy；The working characteristics of uniform air inlet and swirling inlet condition Axial-flow Compressor is contrasted, obtains influence of the eddy flow to axial flow compressor performance and stability.The present invention is simple in construction, it is easy to operate, securely and reliably, pass through the eddy flow in compressor inlet simulation varying strength, structure type, it is easy to carry out the experiment that multi-form eddy flow influences axial flow compressor aerodynamic stability, exploring eddy flow influences the mechanism and rule of Capability of Compressor and stability.
Description
Technical field
The testing stand and test method influenceed the present invention relates to a kind of eddy flow on axial flow compressor aerodynamic stability, belongs to leaf
Wheel mechanical technical field.
Background technology
Aero-engine except by stagnation pressure, stagnation temperature is uneven influenceed in addition to, also suffer from the influence of eddy flow.For fight
For machine, eddy flow is due to the use of S curved intake ports so that air-flow at least faces and turned twice after entering air intake duct, causes gas
The horizontal secondary flow of stream, it is eventually developed to as three-dimensional vortex motion.Eddy flow generally comprises single whirlpool and double whirlpools two types.Eddy flow
There is large effect to aero-engine performance and stability, with the increase of rotating speed, the degree that eddy flow reduces stability margin increases
Greatly；Eddy flow causes thrust to reduce, oil consumption rate increase；Eddy flow is that it can substantially change to the far-reaching main cause of aero-engine
Become operating point and the stability boundaris of compressor；Efficiency and overall pressure tatio of the low-pressure compressor under the influence of single whirlpool in the same direction are above reversely
The situation in single whirlpool.The experiment not influenceed both at home and abroad dedicated for research eddy flow on axial flow compressor aerodynamic stability still at present is put down
Platform.
The content of the invention
Goal of the invention：In order to overcome the deficiencies in the prior art, the present invention provides a kind of eddy flow to axial flow compressor
The testing stand and test method that aerodynamic stability influences, have the characteristics that simple in construction, easy to operate, safe and reliable, Neng Goufang
Just compressor inlet simulate varying strength, structure type eddy flow, without shut down can carry out multi-form eddy flow pair
The experiment that axial flow compressor aerodynamic stability influences.
Technical scheme：To achieve the above object, the technical solution adopted by the present invention is：
The testing stand that a kind of eddy flow influences on axial flow compressor aerodynamic stability, including the air inlet set gradually from front to back
Pipeline, radome fairing, axial flow compressor, discharge duct, choke valve, the first motor, and the air inlet side bottom of admission line
Portion is provided with rotational flow generator；
Wherein, the rotational flow generator includes the second motor, centrifugal compressor and for connecting centrifugal compressor
The generator group section of outlet spiral case and admission line, and the rotating shaft phase of the output shaft of the second motor and centrifugal compressor
Even, the rotating speed for realizing centrifugal compressor by the second motor controls；The generator group section is one section of vertical flat tube
Road, its bottom air inlet connect with the gas outlet of outlet spiral case, and top connects with admission line curved wall；The generator
It is provided with the first rectangle adjustable plate and the second rectangle adjustable plate at the air inlet of group section, both initial levels are arranged symmetrically and one
End is hinged, and is provided with generator group section and is connected to same point with the first rectangle adjustable plate and the second rectangle adjustable plate
Vertical gripper shoe, play a part of support and steady air flow；
The admission line is connected by axial flow compressor with discharge duct, and axial flow compressor front end is set in admission line
The radome fairing for the air-flow that smoothly transits is equipped with, radome fairing is fixed on by pole on the casing of axial flow compressor front end；
The exhaust ports of the discharge duct are provided with hydraulic throttle valve, and discharge duct tail end is provided with choke valve liquid
Pressure control system, axial location of the choke valve along discharge duct is adjusted by choke valve hydraulic control system, to realize axle stream
The flow control of compressor；The output shaft of first motor is connected with the rotating shaft of axial flow compressor, passes through the first driving
Motor realizes the rotating speed control of axial flow compressor.
Preferably, the air inlet flare of the admission line, so as to improve the air inlet effect of admission line.
Preferably, the section of the choke valve is triangular in shape, by adjust axial location of the choke valve along discharge duct come
Change the circulation area between the choke valve conical surface and discharge duct wall, so as to adjust the flow of axial flow compressor.
The test method that a kind of eddy flow influences on axial flow compressor aerodynamic stability, comprises the following steps：
Step 1：Preparation
First rectangle adjustable plate and the second rectangle adjustable plate are rotated to setting position, and pass through choke valve hydraulic control system
The throttle valve position of system adjustment discharge duct, makes exhaust ports in full open position；
Step 2：Variable Control
Start the first motor, and realize that the rotating speed of axial flow compressor controls by the first motor；Pass through second
Motor realizes the rotating speed control of centrifugal compressor, to realize the strength control of admission line inward eddy, and passes through adjustment the
The anglec of rotation of one rectangle adjustable plate and the second rectangle adjustable plate, realize single whirlpool in the same direction in admission line, reversely single whirlpool, to whirlpool this
The switching of three kinds of typical cyclone structures；
Step 3：Parameter measurement
Admission line being measured using steady state pressure measuring system (such as DTC net pressure scannings valve system produced in USA)
Air inlet static pressure, using dynamic pressure measurement instrument (as Belgium production the dynamic pressure measurement instrument of LMS Scada III) measure into
The transient state stagnation pressure of gas port and exhaust outlet, and the transient state stagnation temperature of air inlet and exhaust outlet is measured using fast thermocouple, to obtain
Obtain instantaneous delivery, overall pressure tatio and the efficiency of axial flow compressor；
Axial location of the choke valve along discharge duct is adjusted by choke valve hydraulic control system, changes the choke valve conical surface
With the circulation area between discharge duct wall, to adjust the flow of axial flow compressor, make compressor operatlng polnt to stability boundaris
It is mobile, so as to obtain compressor stability boundaris；Measurement contrasts uniform air inlet and the work of swirling inlet condition Axial-flow Compressor
Characteristic, so as to obtain influence of the eddy flow to axial flow compressor performance and stability influence.
Beneficial effect：The testing stand and experiment that a kind of eddy flow provided by the invention influences on axial flow compressor aerodynamic stability
Method, relative to prior art, there is advantages below：1st, it is simple in construction, it is easy to operate, securely and reliably, it can be repeated, and
Result of the test is directly perceived, comprehensive, reliable；2nd, by the eddy flow in compressor inlet simulation varying strength, structure type, it is easy to carry out
The experiment that multi-form eddy flow influences on axial flow compressor aerodynamic stability, exploration eddy flow influence Capability of Compressor and stability
Mechanism and rule, there is important directive significance to the safe and reliable operation of aero-engine.
Brief description of the drawings
Fig. 1 is the structural representation for the testing stand that a kind of eddy flow of the present invention influences on axial flow compressor aerodynamic stability；
Fig. 2 is the structural representation of centrifugal compressor in the present invention；
Fig. 3 is the structural representation inside generator group section in the present invention；
Fig. 4 a~4c are the state of a control figure inside generator group section in the present invention；
Figure includes：1st, the air inlet of admission line, 2, admission line, 3, radome fairing, 4, pole, 5, axial flow compressor,
6th, discharge duct, 7, choke valve, 8, the rotating shaft of axial flow compressor, the 9, first motor, 10, choke valve hydraulic control system,
11st, the rotating shaft of centrifugal compressor, 12, centrifugal compressor, 13, outlet spiral case, 14, generator group section, the 15, second driving electricity
Machine, 20, vertical gripper shoe, the 21, first rectangle adjustable plate, the 22, second rectangle adjustable plate.
Embodiment
The present invention is further described below in conjunction with the accompanying drawings.
The testing stand influenceed as shown in Figure 1 on axial flow compressor aerodynamic stability for a kind of eddy flow, including from front to back according to
Admission line 2, radome fairing 3, axial flow compressor 5, discharge duct 6, the motor 9 of choke valve 7 and first of secondary setting, and air inlet
The side bottom of air inlet 1 one of pipeline 2 is provided with rotational flow generator；
Wherein, the rotational flow generator includes the second motor 15, centrifugal compressor 12 as shown in Figure 2 and is used for
Connect the generator group section 14 of the outlet spiral case 13 of centrifugal compressor 12 and admission line 2, and the output of the second motor 15
Axle is connected with the rotating shaft 11 of centrifugal compressor 12, and the rotating speed for realizing centrifugal compressor 12 by the second motor 15 controls；
As shown in figure 3, the generator group section 14 is one section of vertical flat tube, its bottom air inlet and outlet spiral case
13 gas outlet connection, and top connects with the curved wall of admission line 2；Set at the air inlet of the generator group section 14
There are the first rectangle adjustable plate 21 and the second rectangle adjustable plate 22, both initial levels are arranged symmetrically and one end is hinged, and are sent out
The vertical branch that same point is connected to the first rectangle adjustable plate 21 and the second rectangle adjustable plate 22 is provided with raw device group section 14
Fagging 20, play a part of support and steady air flow；
The admission line 2 is connected by axial flow compressor 5 with discharge duct 6, and axial flow compressor 5 in admission line 2
Front end is provided with the radome fairing 3 for the air-flow that smoothly transits, and radome fairing 3 is fixed on the machine of the front end of axial flow compressor 5 by pole 4
On casket；
The exhaust ports of the discharge duct 6 are provided with hydraulic throttle valve 7, and the tail end of discharge duct 6 is provided with throttling
Valve hydraulic control system 10, axial location of the choke valve 7 along discharge duct 6 is adjusted by choke valve hydraulic control system 10,
To realize that the flow of axial flow compressor 5 controls；The phase of rotating shaft 8 of the output shaft of first motor 9 and axial flow compressor 5
Even, the rotating speed for realizing axial flow compressor 5 by the first motor 9 controls.
In the present embodiment, the flare of air inlet 1 of the admission line 2；The section of the choke valve 7 is triangular in shape,
Change the stream between the conical surface of choke valve 7 and the wall of discharge duct 6 by adjusting axial location of the choke valve 7 along discharge duct 6
Logical area, so as to adjust the flow of axial flow compressor 5.
In the present embodiment, the axial flow compressor 5 is two-layer configuration, including the two-stage rotor being connected with rotating shaft and fixation
Two-stage stator on casing, corresponding with rotor.
The test method that a kind of eddy flow influences on axial flow compressor aerodynamic stability, comprises the following steps：
Step 1：Preparation
First rectangle adjustable plate 21 and the second rectangle adjustable plate 22 are rotated to setting position, and pass through choke valve hydraulic pressure control
System 10 processed adjusts the position of choke valve 7 of discharge duct 6, makes exhaust ports in full open position；
Step 2：Variable Control
Start the first motor 9, and realize that the rotating speed of axial flow compressor 5 controls by the first motor 9；Pass through
Two motors 15 realize the rotating speed control of centrifugal compressor 12, to realize the strength control of the inward eddy of admission line 2, and pass through
The anglec of rotation of the first rectangle adjustable plate 21 and the second rectangle adjustable plate 22 is adjusted, realizes single whirlpool in the same direction in admission line 2, reversely
Single whirlpool, to whirlpool these three typical cyclone structures switching；
Step 3：Parameter measurement
Admission line 2 is measured using steady state pressure measuring system (DTC net pressure scannings valve system such as produced in USA)
The static pressure of air inlet 1, using dynamic pressure measurement instrument (as Belgium production the dynamic pressure measurement instrument of LMS Scada III) measurement
The transient state stagnation pressure of air inlet and exhaust outlet, and the transient state stagnation temperature of air inlet and exhaust outlet is measured using fast thermocouple, with
Obtain instantaneous delivery, overall pressure tatio and the efficiency of axial flow compressor 5；
Axial location of the choke valve 7 along discharge duct 6 is adjusted by choke valve hydraulic control system 10, changes choke valve
Circulation area between 7 conical surfaces and the wall of discharge duct 6, to adjust the flow of axial flow compressor 5, make compressor operatlng polnt to steady
Boundary Moving is determined, so as to obtain compressor stability boundaris；Measurement contrasts uniform air inlet and swirling inlet condition Axial-flow Compressor 5
Working characteristics, so as to obtain influence of the eddy flow to the performance of axial flow compressor 5 and stability influence.
The testing stand and test method that a kind of eddy flow provided by the invention influences on axial flow compressor aerodynamic stability can be with
Carry out tests below research：
1) experiment of single vortex pair Capability of Compressor and stability influence in the same direction；
2) the reversely experiment of single vortex pair Capability of Compressor and stability influence；
3) experiment of double vortex pair Capability of Compressor and stability influence；
4) eddy flow produces experiment of the dynamic process to Capability of Compressor and stability influence.
Wherein, stable state eddy flow (including in the same direction single whirlpool, reversely single whirlpool, under the typical cyclone structure in three kinds of whirlpool) to compressor
Following steps can be specifically included with the experiment of stability influence：
The first rectangle adjustable plate 21 and the second rectangle adjustable plate 22 are rotated to setting position and (pass through adjustment when A1) starting
Two adjustable plate angles, it is possible to achieve in the same direction single whirlpool, reversely single whirlpool, to whirlpool these three typical cyclone structures switching), such as：
Assuming that axial flow compressor 5 turns clockwise, the first rectangle adjustable plate 21 is threaded to vertically, the second rectangle adjustable plate 22 is threaded to water
It is flat, then reversely single whirlpool is produced in admission line 2；On the contrary then generation single whirlpool in the same direction；When two adjustable plates are threaded to vertical state
Produce in admission line 2 to whirlpool, as shown in Figure 4 a ~ 4c；
A2 axial location of the choke valve 7 along discharge duct 6) is adjusted by choke valve hydraulic control system 10, makes exhaust
Mouth is in full open position；
A3) start the first motor 9, and adjusted axial flow compressor 5 to setting speed by the first motor 9；
A4 the rotating speed of centrifugal compressor 12) is controlled by the second motor 15, realizes the intensity of the inward eddy of admission line 2
Control；
A5 axial location of the choke valve 7 along discharge duct 6) is adjusted by choke valve hydraulic control system 10, reduces row
Gas port circulation area, reduce the flow of axial flow compressor 5；
A6) using the static pressure of air inlet 1 of steady state pressure measuring system measurement admission line 2, using dynamic pressure measurement instrument
The transient state stagnation pressure of air inlet and exhaust outlet is measured, and the transient state stagnation temperature of air inlet and exhaust outlet is measured using fast thermocouple,
To obtain the instantaneous delivery of axial flow compressor 5, overall pressure tatio and efficiency；
A7) repeat step A5-A6, the flow of axial flow compressor 5 is adjusted by choke valve 7, makes compressor operatlng polnt to steady
Determine Boundary Moving, until the unstability of axial flow compressor 5, last stable operating point is exactly that the compressor is steady under current rotating speed
Determine boundary point；
A8 the rotating speed of centrifugal compressor 12) is controlled by the second motor 15, realizes the intensity of the inward eddy of admission line 2
Control, and repeat step A4-A7, so as to obtain the rotating speed line such as compressor under different swirl strengths；
A9 the rotating speed of axial flow compressor 5, and repeat step A4-A8) are controlled by the first motor 9, so as to obtain not
Compressor flow, overall pressure tatio and efficiency under the coaxial speed conditions of flow air compressor 5 under different swirl strengths；
A10 the characteristic of compressor under the conditions of uniform air inlet and stable state swirling inlet) is contrasted, obtains stable state eddy flow to axle stream pressure
The influence that mechanism of qi aerodynamic stability influences.
And the experiment that dynamic eddy flow influences on axial flow compressor aerodynamic stability specifically includes following steps：
The first rectangle adjustable plate 21 and the second rectangle adjustable plate 22 are rotated to setting position and (pass through adjustment when B1) starting
Two adjustable plate angles, it is possible to achieve in the same direction single whirlpool, reversely single whirlpool, to whirlpool these three typical cyclone structures switching), such as：
Assuming that axial flow compressor 5 turns clockwise, the first rectangle adjustable plate 21 is threaded to vertically, the second rectangle adjustable plate 22 is threaded to water
It is flat, then reversely single whirlpool is produced in admission line 2；On the contrary then generation single whirlpool in the same direction；When two adjustable plates are threaded to vertical state
Produced in admission line 2 to whirlpool；
B2 axial location of the choke valve 7 along discharge duct 6) is adjusted by choke valve hydraulic control system 10, makes exhaust
Mouth is in full open position；
B3) start the first motor 9, and adjusted axial flow compressor 5 to setting speed by the first motor 9；
B4 the rotating speed of centrifugal compressor 12) is controlled by the second motor 15, realizes the intensity of the inward eddy of admission line 2
Control；
B5 axial location of the choke valve 7 along discharge duct 6) is adjusted by choke valve hydraulic control system 10, reduces exhaust
Mouth circulation area, reduce the flow of axial flow compressor 5；
B6) by adjusting two adjustable plate angles, single whirlpool, reversely single whirlpool, these three typical eddy flow knots to whirlpool in the same direction are realized
The switching of structure, in this dynamic process, the static pressure of air inlet 1 of admission line 2 is measured using steady state pressure measuring system, using dynamic
State pressure-measuring device measures the transient state stagnation pressure of air inlet and exhaust outlet, and using fast thermocouple measurement air inlet and exhaust outlet
Transient state stagnation temperature, to obtain the instantaneous delivery of axial flow compressor 5, overall pressure tatio and efficiency；
B7) repeat step B5-B6, the flow of axial flow compressor 5 is adjusted by choke valve 7, makes compressor operatlng polnt to steady
Determine Boundary Moving, until compressor instability, then last stable operating point is exactly stabilization of the compressor under current rotating speed
Boundary point (if the operating point is stable operating point, two adjustable plates is rotated to horizontal level)；
B8 the rotating speed of centrifugal compressor 12) is controlled by the second motor 15, realizes the intensity of the inward eddy of admission line 2
Control, and repeat step B4-B7, so as to obtain the rotating speed line such as compressor under different swirl strengths；
B9 the rotating speed of axial flow compressor 5, and repeat step B4-B8) are controlled by the first motor 9, so as to obtain not
Compressor flow, overall pressure tatio and efficiency under the coaxial speed conditions of flow air compressor 5 under different swirl strengths；
B10 the characteristic of compressor under the conditions of uniform air inlet and dynamic swirling inlet) is contrasted, obtains dynamic eddy flow to axle stream pressure
The influence that mechanism of qi aerodynamic stability influences.
Described above is only the preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (4)
1. the testing stand that a kind of eddy flow influences on axial flow compressor aerodynamic stability, it is characterised in that including from front to back successively
Admission line (2), radome fairing (3), axial flow compressor (5), discharge duct (6), choke valve (7), the first motor of setting
(9), and the side bottom of air inlet (1) one of admission line (2) is provided with rotational flow generator；
Wherein, the rotational flow generator includes the second motor (15), centrifugal compressor (12) and for connecting centrifugation pressure
The generator group section (14) of mechanism of qi (12) outlet spiral case (13) and admission line (2), and the output of the second motor (15)
Axle is connected with the rotating shaft (11) of centrifugal compressor (12), and the rotating speed of centrifugal compressor (12) is realized by the second motor (15)
Control；The generator group section (14) is the outlet of one section of vertical flat tube, its bottom air inlet and outlet spiral case (13)
Mouth connection, and top connects with admission line (2) curved wall；Is provided with the air inlet of the generator group section (14)
One rectangle adjustable plate (21) and the second rectangle adjustable plate (22), both initial levels are arranged symmetrically and one end is hinged, and are sent out
It is provided with raw device group section (14) and is connected to same point with the first rectangle adjustable plate (21) and the second rectangle adjustable plate (22)
Vertical gripper shoe (20)；
The admission line (2) is connected by axial flow compressor (5) with discharge duct (6), and radome fairing (3) passes through pole (4)
It is fixed on the casing of axial flow compressor (5) front end；The choke valve (7) is arranged at the exhaust ports of discharge duct (6), and arranges
Feed channel (6) tail end is provided with choke valve hydraulic control system (10), and section is adjusted by choke valve hydraulic control system (10)
Flow axial location of the valve (7) along discharge duct (6)；The output shaft of first motor (9) turns with axial flow compressor (5)
Axle (8) is connected, and the rotating speed for realizing axial flow compressor (5) by the first motor (9) controls.
2. the testing stand that a kind of eddy flow according to claim 1 influences on axial flow compressor aerodynamic stability, its feature exist
In air inlet (1) flare of the admission line (2).
3. the testing stand that a kind of eddy flow according to claim 1 influences on axial flow compressor aerodynamic stability, its feature exist
In the section of the choke valve (7) is triangular in shape, is changed by adjusting axial location of the choke valve (7) along discharge duct (6)
Circulation area between choke valve (7) conical surface and discharge duct (6) wall.
4. the test method that a kind of eddy flow influences on axial flow compressor aerodynamic stability, it is characterised in that comprise the following steps：
Step 1：Preparation
By the first rectangle adjustable plate (21) and the rotation of the second rectangle adjustable plate (22) to setting position, and pass through choke valve hydraulic pressure control
Axial location of system (10) the adjustment choke valve (7) processed along discharge duct (6), makes exhaust ports in full open position；
Step 2：Variable Control
Start the first motor (9), and realize that the rotating speed of axial flow compressor (5) controls by the first motor (9)；Pass through
Second motor (15) realizes the rotating speed control of centrifugal compressor (12), and by adjusting the first rectangle adjustable plate (21) and the
The anglec of rotation of two rectangle adjustable plates (22), realize single whirlpool in the same direction in admission line (2), reversely single whirlpool, to these three typical cases of whirlpool
The switching of cyclone structure；
Step 3：Parameter measurement
Using air inlet (1) static pressure of steady state pressure measuring system measurement admission line (2), measured using dynamic pressure measurement instrument
The transient state stagnation pressure of air inlet and exhaust outlet, and the transient state stagnation temperature of air inlet and exhaust outlet is measured using fast thermocouple, with
Obtain instantaneous delivery, overall pressure tatio and the efficiency of axial flow compressor (5)；Throttling is adjusted by choke valve hydraulic control system (10)
Axial location of the valve (7) along discharge duct (6), realizes the control of axial flow compressor (5) flow, makes compressor operatlng polnt to stabilization
Boundary Moving, so as to obtain compressor stability boundaris；Contrast the work of uniform air inlet and swirling inlet condition Axial-flow Compressor (5)
Make characteristic, so as to obtain influence of the eddy flow to axial flow compressor (5) performance and stability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710809873.0A CN107762955B (en) | 2017-09-11 | 2017-09-11 | The testing stand and test method that eddy flow influences axial flow compressor aerodynamic stability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710809873.0A CN107762955B (en) | 2017-09-11 | 2017-09-11 | The testing stand and test method that eddy flow influences axial flow compressor aerodynamic stability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107762955A true CN107762955A (en) | 2018-03-06 |
| CN107762955B CN107762955B (en) | 2019-01-29 |
Family
ID=61265383
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710809873.0A Active CN107762955B (en) | 2017-09-11 | 2017-09-11 | The testing stand and test method that eddy flow influences axial flow compressor aerodynamic stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107762955B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU542115A1 (en) * | 1975-02-21 | 1977-01-05 | Предприятие П/Я В-2504 | Test bench for axial compressor stage |
| DE102009047195A1 (en) * | 2009-11-26 | 2011-06-01 | Man Diesel & Turbo Se | Pump stroke detection device for turbocompressor e.g. axial compressor, has delta limiter comprising signal input and signal output that are connected with signal output of sensor and signal input of control device, respectively |
| CN202326150U (en) * | 2011-10-14 | 2012-07-11 | 桑增产 | Overall characteristic testing system for axial flow compressor |
| CN103671198A (en) * | 2013-12-25 | 2014-03-26 | 华北电力大学（保定） | Single-stage axial compressor experimental device |
| CN105257428A (en) * | 2015-11-06 | 2016-01-20 | 西南科技大学 | Distributed compression and cyclone ramjet engine |
-
2017
- 2017-09-11 CN CN201710809873.0A patent/CN107762955B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU542115A1 (en) * | 1975-02-21 | 1977-01-05 | Предприятие П/Я В-2504 | Test bench for axial compressor stage |
| DE102009047195A1 (en) * | 2009-11-26 | 2011-06-01 | Man Diesel & Turbo Se | Pump stroke detection device for turbocompressor e.g. axial compressor, has delta limiter comprising signal input and signal output that are connected with signal output of sensor and signal input of control device, respectively |
| CN202326150U (en) * | 2011-10-14 | 2012-07-11 | 桑增产 | Overall characteristic testing system for axial flow compressor |
| CN103671198A (en) * | 2013-12-25 | 2014-03-26 | 华北电力大学（保定） | Single-stage axial compressor experimental device |
| CN105257428A (en) * | 2015-11-06 | 2016-01-20 | 西南科技大学 | Distributed compression and cyclone ramjet engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107762955B (en) | 2019-01-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107505138B (en) | A kind of complicated distortion generator for Compressor Stability test | |
| CN106198034A (en) | A kind of rotary punching Compressor test system | |
| CN106153346A (en) | A kind of inflatable vane type swirl flow distortion generator and method for generation | |
| CN206054385U (en) | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance | |
| CN104895841B (en) | Rectifier, flow passage structure, combined compressor, aero gas turbine engine | |
| CN104533816B (en) | A kind of centrifugal compressor radial diffuser assay device and test method thereof | |
| CN107762956B (en) | The testing stand and test method that high-temperature steam influences Stability of Axial compressors | |
| CN107676272B (en) | A kind of fast adjuster of Working Conditions of Centrifugal Injection Pumps | |
| CN108661947A (en) | Using the axial flow compressor blade of Condar jet and using its axial flow compressor | |
| CN107762955B (en) | The testing stand and test method that eddy flow influences axial flow compressor aerodynamic stability | |
| CN104153821B (en) | A kind of variable geometry turbine with variable stator vane angle from bleed-jet structure | |
| CN106697306B (en) | Compressing surface Secondary Flow self-loopa pneumatic type variable geometry inlet at the same level and control method | |
| CN205422838U (en) | Become turbine how much with wavy leading edge sunk structure of moving vane | |
| CN110360157A (en) | A kind of gas turbine blower shrouding strip of space structure | |
| CN105388018B (en) | Engine total head difference air flue tumble flow experimental rig | |
| CN104061062B (en) | Intake and exhaust with double venturi regulate system | |
| CN203404103U (en) | Efficient energy-saving high-speed compressor | |
| CN206972617U (en) | A kind of guide vane of water pump cell structure | |
| CN205823750U (en) | Radially adjustable inlet guide vane for radial-flow gas turbine | |
| CN105020006B (en) | A kind of the compressed air auxiliary device and control method of boosting internal combustion engine | |
| CN209198041U (en) | A kind of direct current of band bypass blows formula gust wind tunnel | |
| CN203404117U (en) | Efficient energy-saving double-suction fan | |
| CN207920736U (en) | Fanjet core engine for aviation power field | |
| CN113944656B (en) | Variable cross-section end wall pre-rotation guide vane pipeline structure | |
| CN205446193U (en) | Turbo charger compressor expands steady structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |