CN115788936A - Aerodynamic force analysis method of vaneless diffuser - Google Patents
Aerodynamic force analysis method of vaneless diffuser Download PDFInfo
- Publication number
- CN115788936A CN115788936A CN202211711478.6A CN202211711478A CN115788936A CN 115788936 A CN115788936 A CN 115788936A CN 202211711478 A CN202211711478 A CN 202211711478A CN 115788936 A CN115788936 A CN 115788936A
- Authority
- CN
- China
- Prior art keywords
- pressure pulsation
- aerodynamic force
- stall
- signal
- pressure
- 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
- 238000004458 analytical method Methods 0.000 title claims description 33
- 230000010349 pulsation Effects 0.000 claims abstract description 71
- 238000004364 calculation method Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 18
- 238000012545 processing Methods 0.000 claims abstract description 11
- 238000001914 filtration Methods 0.000 claims description 16
- 238000010219 correlation analysis Methods 0.000 claims description 9
- 238000010586 diagram Methods 0.000 description 6
- 238000001228 spectrum Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000012800 visualization Methods 0.000 description 1
Images
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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention provides a method for analyzing aerodynamic force of a vaneless diffuser, belonging to the technical field of mechanical dynamics and comprising the following steps of: selecting a pressure pulsation signal of a signal source; processing the pressure pulsation signal; analyzing the pressure pulsation signal; calculating stall frequency and stall group number; determining a circumferential pressure distribution; the radial aerodynamic force is calculated. And the rotating stall frequency identification, the stall group number determination, the circumferential pressure distribution determination and the aerodynamic force calculation can be realized only by a few measuring point pressure pulsation signals. Selecting pressure pulsation signals in the circumferential direction of the section of the diffuser, and then sequentially processing and analyzing the pressure pulsation signals to obtain accurate results such as rotating stall frequency, stall group number, aerodynamic force and the like; and then, the circumferential pressure distribution of the action area of the radial aerodynamic force is integrated, namely, the circumferential pressure distribution of the diffuser manhole is integrated, the radial aerodynamic force is calculated, the influence generated by the rotating stall of the vaneless diffuser is really reflected, the calculated amount is less, and the application range is wide.
Description
Technical Field
The invention belongs to the technical field of mechanical dynamics, and particularly relates to a method for analyzing aerodynamic force of a vaneless diffuser.
Background
In a centrifugal compressor, in order to decelerate an air flow having a relatively high speed coming out of an impeller and to effectively convert kinetic energy into pressure energy, a diffuser structure is often provided at an outlet of the impeller. The vaneless diffuser has better performance under variable working conditions, is simple to process and has larger flow loss. However, in order to meet the operation requirement of wide working conditions on site, the compressor inevitably operates in a certain stage of small flow area, so that the airflow rotation separation phenomenon is formed in the vaneless diffuser of the stage, and the rotating stall is generated. Severe rotating stall can result in increased rotor vibration and affect safe operation of the compressor. In the past, rotor vibration caused by rotating stall can only be analyzed from the flow field angle, and the rotor vibration response analysis cannot be quantified, wherein one of the most important reasons is that aerodynamic force caused by rotating stall cannot be accurately calculated.
At present, the commonly used calculation method is based on a simple formula of force and pressure, and then is assisted by the correction of an empirical coefficient. Sometimes, other fault frequency components are mixed in the calculation method, the rotating stall frequency is difficult to accurately identify, and the influence generated by the rotating stall of the vaneless diffuser is difficult to truly reflect.
Disclosure of Invention
In order to solve the problems that the rotating stall frequency is difficult to accurately identify by the calculation method in the prior art, the influence generated by the rotating stall of the vaneless diffuser is difficult to truly reflect, and the like, the invention provides the aerodynamic force analysis method of the vaneless diffuser. The specific technical scheme is as follows:
a vaneless diffuser aerodynamic force analysis method comprises the following steps: selecting a pressure pulsation signal of a signal source; processing the pressure pulsation signal; analyzing the pressure pulsation signal; calculating stall frequency and stall group number; determining a circumferential pressure distribution; the radial aerodynamic force is calculated.
In addition, the method for analyzing the aerodynamic force of the vaneless diffuser in the technical scheme provided by the invention can also have the following additional technical characteristics:
optionally, the pressure pulsation signals of the two signal sources are selected.
Optionally, selecting the pressure pulsation signal of the signal source further includes: one of the pressure pulsation signals is used to establish the time domain waveform of the pressure field, and the other pressure pulsation signal is used to calculate the phase of the pressure.
Optionally, processing the pressure pulsation signal further comprises: removing the direct current component of the pressure pulsation signal; the pressure pulsation signal is filtered.
Optionally, the pressure pulsation signal is filtered using low pass filtering.
Optionally, processing the pressure pulsation signal further comprises: frequency components higher than 1 times the frequency of the pressure pulsation signal are filtered.
Optionally, analyzing the pressure pulsation signal further comprises: and performing autocorrelation analysis and cross-correlation analysis on the pressure pulsation signal.
Optionally, analyzing the pressure pulsation signal further comprises: the time difference between two peaks is delta t in the autocorrelation analysis result 1 Taking the time difference between the first positive peak and 0 in the cross-correlation analysis result as delta t 2 And calculating the stall frequency and the number of stall groups.
Optionally, the vaneless diffuser aerodynamic force analysis method further includes: and selecting at least two pulse signals as measuring points for checking calculation.
Optionally, the circumferential angle between two adjacent measuring points is not greater than 90 °.
Compared with the prior art, the aerodynamic force analysis method of the vaneless diffuser has the following beneficial effects:
the analysis method provided by the invention can realize rotating stall frequency identification, stall cluster number determination, circumferential pressure distribution determination and aerodynamic force calculation by only needing fewer measuring point pressure pulsation signals, has less calculation amount and high calculation efficiency, is simultaneously suitable for pressure pulsation data obtained by numerical simulation and test, has lower requirements on the compressor structure and the number of sensors, and has wide application range. Selecting pressure pulsation signals in the circumferential direction of the section of the diffuser, and then sequentially processing and analyzing the pressure pulsation signals to obtain accurate results such as rotating stall frequency, stall group number, aerodynamic force and the like; and integrating the circumferential pressure distribution of the action area of the radial aerodynamic force, namely integrating the circumferential pressure distribution at the manhole of the diffuser to calculate the radial aerodynamic force, thereby truly reflecting the influence generated by the rotating stall of the vaneless diffuser.
Drawings
FIG. 1 is a flow chart of a vaneless diffuser aerodynamic analysis method according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of signal autocorrelation analysis for a vaneless diffuser aerodynamic analysis method according to one embodiment of the present disclosure;
FIG. 3 is a schematic diagram of a cross-correlation analysis of signals for a vaneless diffuser aerodynamic analysis method according to an embodiment of the present invention;
FIG. 4 is a signal circumferential pressure profile of a vaneless diffuser aerodynamic analysis method according to one embodiment of the present disclosure;
FIG. 5 is a flow chart of a vaneless diffuser aerodynamic analysis method according to another embodiment of the present disclosure;
FIG. 6 is a schematic view of the site placement locations in the cited references;
FIG. 7 is a time domain signal diagram before and after filtering at point 1;
FIG. 8 is a time domain signal diagram before and after filtering at point 2;
FIG. 9 is a spectrum diagram before and after filtering at point 1;
FIG. 10 is a graph of the spectrum before and after filtering at point 2;
FIG. 11 is a spectrum diagram before and after filtering at point 1;
FIG. 12 is a graph of the spectrum before and after filtering at point 2;
FIG. 13 is a pressure profile in the circumferential direction of the signals in the cited reference;
fig. 14 is a flow chart of a method of analyzing aerodynamic force of a vaneless diffuser according to yet another embodiment of the present disclosure.
Detailed Description
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely for convenience of description and simplification of the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and encompass, for example, both fixed and removable connections or integral connections; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Referring to fig. 1 in combination, according to an embodiment of the present application, a vaneless diffuser aerodynamic analysis method includes: selecting a pressure pulsation signal of a signal source; processing the pressure pulsation signal; analyzing the pressure pulsation signal; calculating stall frequency and stall group number; determining a circumferential pressure distribution; the radial aerodynamic force is calculated. The accurate rotating stall frequency, stall group number, aerodynamic force and other results can be obtained by selecting the pressure pulsation signal in the circumferential direction of the section of the diffuser and then sequentially processing and analyzing the pressure pulsation signal; and integrating the circumferential pressure distribution of the action area of the radial aerodynamic force, namely integrating the circumferential pressure distribution at the manhole of the diffuser to calculate the radial aerodynamic force, thereby truly reflecting the influence generated by the rotating stall of the vaneless diffuser. The analysis method can realize rotating stall frequency identification, stall cluster number determination, circumferential pressure distribution determination and aerodynamic force calculation by only needing fewer measuring point pressure pulsation signals, has less calculation amount and high calculation efficiency, is suitable for pressure pulsation data obtained by numerical simulation and test, and has wide application range.
It should be noted that the aerodynamic force is generated mainly due to the rotating stall inside the vaneless diffuser, which causes the circumferential pressure to be uneven at the diffuser inlet and the impeller outlet, and further generates a radial aerodynamic force. As shown in fig. 4, the circumferential pressure distribution at the diffuser inlet can be represented in polar plots, with the pressure distribution superimposed on a reference pressure level to improve the appearance of the graph, clearly showing the single lobe characteristic of stall for verification and comparison.
As an example, the pressure pulsation signals of two signal sources are selected. The number of stall groups can be determined by selecting the pressure pulsation signal data of two signal sources and the phase relation between the pressure pulsation time domain signals of two measuring points, the radial aerodynamic force is calculated, the calculated amount is reduced, and the calculation efficiency is improved.
It should be noted that the pressure pulsation signals of a plurality of signal sources can be selected, only the pressure pulsation signals of two of the signal sources are analyzed, and the radial aerodynamic force is calculated; the remaining signals can be used to verify the accuracy and applicability of the analytical method.
One of the pressure pulsation signals is used to establish the time domain waveform of the pressure field, and the other pressure pulsation signal is used to calculate the phase of the pressure. The phase relation between pressure pulsation time domain signals is obtained by establishing a pressure field and a time domain waveform and calculating the phase of pressure, so that the number of stall groups can be conveniently determined.
As another embodiment, as shown in fig. 5, the direct current component of the pressure pulsation signal is removed; the pressure pulsation signal is filtered. By removing the direct current component of the pulsation signal and filtering the pressure pulsation signal, the interference of the direct current component and the generation of unnecessary electromagnetic fields to other signals is avoided.
And filtering the pressure pulsation signal by adopting a low-pass filtering method. By adopting a low-pass filtering method, the passing of signals with frequencies higher than a cut-off frequency is reduced, low-frequency signals are allowed to pass, and the filtering effect is ensured.
Specifically, the pressure pulsation signal is filtered using a low pass filter.
Frequency components higher than 1 times the frequency of the pressure pulsation signal are filtered. By filtering out frequency components higher than 1 time of frequency conversion of the pressure signal, frequency components less than or equal to 1 time of frequency conversion of the pressure signal are reserved.
Specifically, the frequency of the pressure pulsation signal is the reciprocal of the rotation speed of the test bed.
As another example, as shown in fig. 2 and 3, the pressure pulsation signal is subjected to autocorrelation analysis and cross-correlation analysis. The autocorrelation analysis result delta t is obtained by carrying out autocorrelation analysis and cross-correlation analysis on the two groups of pressure pulsation signals 1 And cross-correlation analysis result Δ t 2 And calculating the stall frequency and the stall group number according to a formula.
The time difference between two peaks is delta t in the autocorrelation analysis result 1 Taking the time difference between the first positive peak and 0 in the cross-correlation analysis result as delta t 2 Calculating the stall frequency f according to equation 1 stall Calculating the number N of stall clusters according to the formula 2 cell 。
Radial aerodynamic force F stall The value of (d) is obtained by integrating the circumferential pressure distribution of the aerodynamic force application region, as shown in equation 3. Wherein p (ψ) is a pressure distribution in the circumferential direction; psi is a circumferential angle; b is a mixture of diff Is the diffuser inlet width; r diff Is the diffuser inlet radius.
For discrete data points, the radial aerodynamic force F stall The calculation method of (c) is shown in equation 4. In the formula, N step For the number of time steps in the stall burst operating cycle,
f cell in order to complete the pulsation cycle of the stall mass,
dt is the time step; and p (i) is the pressure value corresponding to the ith time step.
According to equations 5 and 6, the radial aerodynamic force is resolved into horizontal x and vertical y directions,obtain horizontal aerodynamic force FX stall And vertical aerodynamic force FY stall 。
And selecting at least two pulse signals as measuring points for checking calculation. The accuracy and the applicability of the calculation result are ensured by selecting at least two pulse signal checking calculation results.
The circumferential angle between two adjacent measuring points is not more than 90 degrees. The circumferential angle between two adjacent measuring points is smaller than or equal to 90 degrees, so that the condition of abnormal stall group number is avoided, the checking result is not matched with the calculation result, and the accuracy and the credibility of the checking result are ensured.
The test data are the results in the reference "rolling Stall Induced Non-Synchronous Blade visualization Analysis for an unhhreshold Industrial central throttle Compressor". The measuring point arrangement is shown in FIG. 6, and the number of the stall clusters is 5 and the stall frequency is 21.9Hz through the analysis of the pressure pulsation signals of the measuring points.
As shown in fig. 14, the data in the reference document is analyzed and verified again according to the method in the patent, the pressure pulsation signals of two measuring points are selected, taking measuring point 1 and measuring point 2 as an example, the signals are firstly filtered, and time domain signals before and after filtering are compared, as shown in fig. 7 and fig. 8. The rotating speed of the experimental table is 5610r/min, namely the frequency is 93.5Hz. Therefore, the signal is low-pass filtered to filter out frequency components greater than 93.5Hz, as shown in FIGS. 9 and 10. Then, the analysis of the auto-correlation and the cross-correlation is performed thereon, as shown in fig. 11 and 12.
And calculating the stall frequency and the number of stall groups according to a formula 1 and a formula 2. Meanwhile, different measuring point signals are selected for checking calculation, and the result is shown in table 1. The stall frequency calculated by the method provided by the application is about 22Hz, the number of stall clusters is 5, and the result is consistent with the result of the reference. Moreover, from the table, it is found that the angle between two measuring points is too large (greater than 90 °), which results in abnormal results, so that when the monitoring points are set, the angle between two measuring points should be less than or equal to 90 °.
Table one:
table 1 shows the data obtained by the analysis method of the present application, and it can be seen from table 1 that when the circumferential angle between the measuring points 4 and 5 is greater than 90 degrees, the number of stall clusters is abnormal, inconsistent with the results of other groups, and mismatched with the axial pressure distribution map. The circumferential pressure distribution at the diffuser inlet was plotted, and as shown in fig. 13, the reference pressure was selected to be 10000Pa. The circumferential pressure distribution is clearly seen in the figure as a "5 lobe" distribution, clearly showing the effect of the 5 stall masses.
The radial aerodynamic force is-6.19N according to the formula (4), and the aerodynamic forces in the horizontal direction and the vertical direction are respectively 1.33N and-1.6N according to the formula 5 and the formula 6.
It is readily understood by a person skilled in the art that the advantageous ways described above can be freely combined, superimposed without conflict.
The present invention is not intended to be limited to the particular embodiments shown and described, but is to be accorded the widest scope consistent with the principles and novel features herein disclosed. The foregoing is only a preferred embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present application, and these modifications and variations should also be considered as the protection scope of the present application.
Claims (10)
1. A vaneless diffuser aerodynamic force analysis method, characterized in that it comprises:
selecting a pressure pulsation signal of a signal source;
processing the pressure pulsation signal;
analyzing the pressure pulsation signal;
calculating stall frequency and stall group number;
determining a circumferential pressure distribution;
the radial aerodynamic force is calculated.
2. The method of analyzing aerodynamic force of a vaneless diffuser according to claim 1, wherein:
and selecting pressure pulsation signals of the two signal sources.
3. The method of claim 2, wherein selecting the pressure pulsation signal from the signal source further comprises:
one of the pressure pulsation signals is used to establish the time domain waveform of the pressure field, and the other pressure pulsation signal is used to calculate the phase of the pressure.
4. The vaneless diffuser aerodynamic analysis method of claim 1, wherein processing the pressure pulsation signal further comprises:
removing the direct current component of the pressure pulsation signal;
the pressure pulsation signal is filtered.
5. The method of claim 4, wherein the method comprises:
and filtering the pressure pulsation signal by adopting a low-pass filtering method.
6. The vaneless diffuser aerodynamic analysis method of claim 5, wherein processing the pressure pulsation signal further comprises:
frequency components higher than 1 times the frequency of the pressure pulsation signal are filtered.
7. The method of analyzing the aerodynamic force of a vaneless diffuser of claim 1, wherein analyzing the pressure pulsation signal further comprises:
and performing autocorrelation analysis and cross-correlation analysis on the pressure pulsation signal.
8. The method of analyzing the aerodynamic force of a vaneless diffuser according to claim 7, wherein analyzing the pressure pulsation signal further comprises:
the time difference between two peaks is Δ t in the autocorrelation analysis result 1 ；
Taking the time difference between the first peak value in the forward direction and 0 in the cross-correlation analysis result as delta t 2 And calculating the stall frequency and the number of stall groups.
9. The vaneless diffuser aerodynamic analysis method of claim 1, further comprising:
and selecting at least two pressure pulsation signals as measuring points for checking calculation.
10. The method of claim 9, wherein the method comprises:
the circumferential angle between two adjacent measuring points is not more than 90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211711478.6A CN115788936A (en) | 2022-12-29 | 2022-12-29 | Aerodynamic force analysis method of vaneless diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211711478.6A CN115788936A (en) | 2022-12-29 | 2022-12-29 | Aerodynamic force analysis method of vaneless diffuser |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115788936A true CN115788936A (en) | 2023-03-14 |
Family
ID=85428185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211711478.6A Pending CN115788936A (en) | 2022-12-29 | 2022-12-29 | Aerodynamic force analysis method of vaneless diffuser |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115788936A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116358823A (en) * | 2023-05-26 | 2023-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
-
2022
- 2022-12-29 CN CN202211711478.6A patent/CN115788936A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116358823A (en) * | 2023-05-26 | 2023-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
| CN116358823B (en) * | 2023-05-26 | 2023-08-18 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7409854B2 (en) | Method and apparatus for determining an operating status of a turbine engine | |
| Megerle et al. | Numerical and experimental investigation of the aerodynamic excitation of a model low-pressure steam turbine stage operating under low volume flow | |
| CN115788936A (en) | Aerodynamic force analysis method of vaneless diffuser | |
| Bianchini et al. | Some guidelines for the experimental characterization of vaneless diffuser rotating stall in stages of industrial centrifugal compressors | |
| CN101629572A (en) | Stall and surge detection system and method | |
| CN108699966B (en) | Surge detection method and surge detection device for supercharger | |
| CN104763663B (en) | The determination method and system in compressor operating space based on variable parameter operation | |
| RU2011147173A (en) | METHOD FOR VIBRATION DIAGNOSTICS AND FORECASTING OF Sudden Failure OF ENGINE AND CARRIER | |
| US20160320767A1 (en) | Apparatus and method for detecting the current damaged state of a machine | |
| Cravero et al. | Numerical prediction of tonal noise in centrifugal blowers | |
| Abdelhamid et al. | Distinctions between two types of self excited gas oscillations in vaneless radial diffusers | |
| CN112417774A (en) | Method and device for identifying rotating stall of compressor and computer equipment | |
| Reggio et al. | Vibrational analysis for surge precursor definition in gas turbines | |
| US11210435B2 (en) | Method of designing and producing a turbine | |
| US20150354446A1 (en) | Acoustic measuring device | |
| Megerle et al. | Unsteady Aerodynamics of Low-Pressure Steam Turbines Operating Under Low Volume Flow | |
| Garcia et al. | Dynamical system analysis of unstable flow phenomena in centrifugal blower | |
| Kissner et al. | Assessment of a 2D synthetic turbulence method for predicting the ACAT1 fan's broadband noise | |
| CN116663202B (en) | Checking method of performance simulation model of multistage axial flow compressor | |
| Mileshin et al. | Numerical and experimental analysis of radial clearance influence on rotor and stator clocking effect by example of model high loaded two stage compressor | |
| Zemp et al. | Unsteady CFD investigation on inlet distortion in a centrifugal compressor | |
| Heinz et al. | Impact of Mistuning on the Vibration Behaviour of the Last Stage in a Model Three Stage Low Pressure Steam Turbine | |
| CN104334849A (en) | Exhaust-gas turbocharger | |
| CN110966100B (en) | Combustion oscillation monitoring device and method | |
| CN108798795B (en) | Turbulence sensor for a turbomachine compressor |
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 | ||
| CB02 | Change of applicant information |
Address after: 110869 No. 16 A Development Road, Shenyang Economic and Technological Development Zone, Liaoning Province Applicant after: Shenyang Blower Works Group Corp. Address before: 110869 No. 16 A Development Road, Shenyang Economic and Technological Development Zone, Liaoning Province Applicant before: SHENYANG BLOWER WORKS Group Corp. |
|
| CB02 | Change of applicant information |