CN113417883B - Detection device and air compressor - Google Patents
Detection device and air compressor Download PDFInfo
- Publication number
- CN113417883B CN113417883B CN202110978957.3A CN202110978957A CN113417883B CN 113417883 B CN113417883 B CN 113417883B CN 202110978957 A CN202110978957 A CN 202110978957A CN 113417883 B CN113417883 B CN 113417883B
- Authority
- CN
- China
- Prior art keywords
- probe
- support plate
- compressor
- groove
- channel
- 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
- 238000001514 detection method Methods 0.000 title claims abstract description 15
- 239000000523 sample Substances 0.000 claims abstract description 89
- 238000013461 design Methods 0.000 description 19
- 238000005259 measurement Methods 0.000 description 9
- 238000000926 separation method Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 230000009747 swallowing Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000000740 bleeding effect Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The detection device arranged in the compressor comprises a support plate and a probe, wherein the support plate comprises a groove and a gas-guiding channel, the groove is arranged at the tail edge and extends from the tail edge to the front edge, and the gas-guiding channel is used for guiding gas to the outside of the compressor; the probe comprises a probe body and a probe body, the probe body is embedded into the groove and defines a flow channel with the groove, the flow channel is communicated with the air entraining channel, and the probe is positioned outside the support plate. The detection device can safely and reliably detect the air flow parameters such as pressure and the like. A compressor is also provided.
Description
Technical Field
The invention relates to the field of gas compressors, in particular to the field of gas compressor support plates.
Background
The turbofan engine is one of aeroengines, is generally a birotor engine and mainly comprises a fan supercharging stage, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine. A typical civil aircraft engine is shown in schematic form in figure 1, with an air stream flowing from the engine inlet and through a fan 1. Part of the airflow flows into the outer duct 2 through the splitter ring, part of the airflow flows into the inner duct, flows into the high-pressure compressor 4 through the support plate 3, and then is discharged out of the engine body through the combustion chamber 5 and the turbine 6.
When the engine is tested and operated, the air flow parameters of the cross section of each typical position need to be monitored in real time. For the inlet position of the high-pressure compressor, a pressure probe needs to be installed to measure the total pressure of the inlet position, the total pressure is fed back to the engine control, and the engine control is combined with other monitoring parameters to jointly judge the running condition of the engine, so that the pressure measurement of the inlet section is of great importance.
The traditional probe is fixedly arranged in the middle of a support plate channel through a support rod, and the support plate is a connecting structure of a low-pressure air compressor and a high-pressure air compressor and has a force bearing effect. However, the conventional probe mounting method has two problems: firstly, along with the continuous change of the flying environment of the airplane, such as the occurrence of various situations of rain absorption, ice swallowing, sand swallowing, bird sucking and the like of the airplane, foreign matters are knocked on the probe, so that the reading of the probe is invalid and even damaged, and damaged probe fragments are sucked into the air compressor, thereby possibly bringing disasters; and secondly, the probe is arranged in the middle of the support plate channel, needs a larger device for installation, and is easy to block the air-entraining channel, thereby affecting the performance of the whole air compressor and the engine.
In addition, due to the requirements of engine bearing force and the like, the support plate is often designed to be thicker, and the flow loss of airflow flowing through the tail edge of the support plate is larger. The traditional support plate design does not consider the flow loss, or an integral support plate is designed into two rows of support plate blades, or a suction small hole device and a suction boundary layer are arranged at the positions of the support plate blade roots, but the design structures of the improved support plates are complex, and the improved support plates deviate from the design scheme and still have influence on the performance of the downstream compressor.
Disclosure of Invention
An object of the present invention is to provide a detection device capable of effectively monitoring airflow parameters safely and reliably and effectively reducing airflow loss.
The detection device comprises a support plate and a probe, wherein the support plate comprises a groove and a gas-guiding channel, the groove is arranged at the tail edge and extends from the tail edge to the front edge, and the gas-guiding channel is used for guiding gas to the outside of the gas compressor; the probe comprises a probe body and a probe body, the probe body is embedded into the groove and defines a flow channel with the groove, the flow channel is communicated with the air entraining channel, and the probe is positioned outside the support plate.
In one or more embodiments, the probe body is fixedly connected with the groove surface of the groove in the span direction or the thickness direction of the support plate.
In one or more embodiments, the probe is integrally formed with the strip.
In one or more embodiments, the groove extends along a chordwise direction and a spanwise direction of the support plate, a ratio α of a length of the probe in the chordwise direction to a length of the support plate in the chordwise direction is in a range of 0.15 to 0.3, and a ratio β of a length of the probe in the spanwise direction to a length of the support plate in the spanwise direction is in a range of 0.2 to 0.8.
It is a further object of the present invention to provide a compressor comprising a high pressure compressor and a low pressure compressor, between which the above-mentioned detecting means are arranged.
According to the detection device, the grooves are formed in the support plate, and the probes are arranged in the grooves of the support plate to detect airflow data such as pressure, foreign matter erosion of raindrops, hailstones and gravels can be effectively avoided, the possibility of damage of the probes is reduced, and the safety and reliability of the probes are ensured; in addition, a flow channel formed by the probe body and the groove can effectively extract low-speed airflow at the tail edge of the support plate, so that airflow separation is eliminated, airflow loss is reduced, and the performance of the compressor is improved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a conventional turbofan engine;
FIG. 2 is a schematic view of a conventional strut profile and flow conditions;
FIG. 3 is a cross-sectional view of the plate taken along line B-B of FIG. 1;
FIG. 4 is a cross-sectional view taken along the line A-A in FIG. 1;
FIG. 5 is a graph comparing the results of the probe measurements with the design requirements for cross-sectional gas flow parameters.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention. It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the invention as it is actually claimed.
Referring to fig. 1, in the conventional compressor, a support plate 3 is used as a connecting structure of the low-pressure compressor and the high-pressure compressor, and has a force bearing effect. One common vane pattern and flow pattern is shown in FIG. 2, where a flowing gas stream 60 flows around the periphery of the plate 3. The traditional airborne probe is fixedly arranged in the middle of a channel formed by the plurality of support plates 3 through a support rod so as to detect the air flow parameters in the channel. The probe located in the outer passage is susceptible to external shock, and unavoidable foreign objects such as raindrops, hailstones, sand, etc. may damage the probe. In addition, because the airflow at the tail edge of the support plate is the main flow pressure of the inlet of the compressor, and the airflow is subjected to the supercharging action of the fan and the supercharging stage, the pressure is usually 1.5-2 times of atmospheric pressure and higher than the external atmospheric pressure, large flow separation is generated at the tail edge of the support plate, accumulated tail edge low-speed airflow vortices 50 are generated, a wake is formed, so that the flow loss is large when the airflow flows through the support plate, and the performance of the whole compressor is influenced.
The detection device can effectively avoid the probe from being damaged, ensures the safety and reliability of the probe, can eliminate low-speed airflow vortex at the tail edge of the supporting plate and reduces airflow loss.
It should be noted that the extension direction of the support plate mentioned in the present disclosure refers to the support plate along the radial direction of the compressor; the chord direction of the support plate is the direction from the front edge to the rear edge of the support plate, namely the left-right direction shown in FIG. 2; the thickness direction of the fulcrum plate is a normal direction perpendicular to the chordwise direction, i.e., the up-down direction shown in fig. 2. Fig. 3 is a sectional view taken along the direction B-B in fig. 1, and fig. 4 is a sectional view taken along the direction a-a in fig. 1 on the basis of fig. 3, and therefore fig. 4 shows only a part of the probe configuration.
Referring to fig. 3 and 4, the detection device is arranged in the compressor and comprises a support plate 3 and a probe 9. The strip 3 comprises a recess 31 and a bleed air channel (not shown) located inside the strip 3 for bleeding air to the outside of the compressor. The groove 31 is disposed at the trailing edge of the strip 3 and extends from the trailing edge in the direction of the leading edge.
The groove 31 is provided in the embodiment shown in fig. 3, but not limited to, extending along the chord direction of the support plate, and in other embodiments, the extending direction of the groove 31 may also extend from the tail edge of the support plate to the front edge of the support plate by deviating from the chord direction.
The probe 9 comprises a probe 92 and a probe 91, the probe 91 is embedded in the groove 31, and the probe 92 is positioned outside the support plate 3 and used for detecting air flow parameters such as pressure in the section of the compressor. The main part of the probe 9, namely the probe body 91, is embedded into the support plate 3, so that the probe can be prevented from being corroded by raindrops, hailstones and gravels, the possibility of overall damage of the probe 9 is reduced, the probe can be used for a long time, the safety and the reliability of the probe are improved, and the pressure change of the inlet section of the compressor can be monitored safely and efficiently.
It should be noted that the gas flow parameter measured by the single probe 9 is only the parameter value of a certain measuring point of the cross section. In actual measurement, firstly, detailed measurement is carried out on the cross-section airflow parameters at the beginning of an engine test, and the real airflow parameters P1 at the position are obtained by arranging N × M measuring points. Meanwhile, the probes 9 are arranged, the airflow parameter P2 of a single measurement point is obtained through the probe 9, and the relationship between P1 and P2, such as a linear relationship or other fitting relationships, is established by carrying out tests under different working conditions and different environments, which is not described herein again. Therefore, when the subsequent engine is actually operated, the true air flow parameter P1 of the inlet section of the compressor can be obtained by only measuring the P2 acquired by the probe 9 according to the mathematical relationship established by the P1 and the P2.
The probe 91 is embedded in the recess 31 of the plate 3 and defines with the recess 31 a flow channel 95, the flow channel 95 communicating with the bleed air passage inside the plate 3. The flow channel 95 can draw in low velocity air flow at the trailing edge of the strip 3 to eliminate trailing edge flow separation.
The principle of the flow channel 95 is understood with reference to fig. 2. Because the airflow at the tail edge of the support plate 3 is the main flow pressure of the inlet of the compressor, and the airflow generates low-speed airflow when flowing through the tail edge of the support plate, based on the pressure difference between the high-pressure airflow at the flow channel 95 communicated with the bleed air channel and the low-pressure airflow at the tail edge of the support plate, the flow channel 95 can guide the low-speed airflow in the low-pressure band at the position, so that the low-speed airflow vortex 50 at the tail edge of the support plate is extracted, the low-speed airflow is guided into the flow channel 95 to the bleed air channel and finally flows out of the support plate, the airflow separation at the tail edge of the support plate is eliminated, and the airflow loss is reduced.
In one embodiment, the probe 91 is embedded in the groove 31, and the probe 91 is fixedly connected with the groove surface of the groove 31 in the spanwise direction or the thickness direction of the support plate 3. For example, the probe 91 and the bracket 3 are fixedly connected by an integral method, such as welding. In the embodiment shown in fig. 3 and 4, the probe 91 is integrally formed with the strip 3 in the span-wise direction of the strip 3, while defining a flow channel 95 with the strip 3 in the chord-wise and thickness directions. The flow channel 95 communicates with the bleed air channel inside the strip 3 to communicate with the outside atmosphere. Therefore, the flow channel 95 formed at the tail edge of the support plate can extract the low-speed airflow gathered at the tail edge of the support plate, and the low-speed airflow enters the air-entraining channel in the support plate 3 through the flow channel 95 and is discharged, so that the phenomenon of airflow separation at the tail edge is eliminated, the airflow loss is effectively reduced, and the overall performance of the compressor is improved.
In one embodiment, the groove 31 extends along the chord length direction of the support plate 3, and the ratio alpha of the length of the probe 91 in the chord direction to the length of the support plate 3 in the chord length direction is in the range of 0.15-0.3; the groove 31 extends along the spanwise direction of the support plate 3, and the ratio beta of the length of the probe 91 in the spanwise direction to the length of the support plate 3 in the spanwise direction is 0.2-0.8.
As can be understood by referring to fig. 3, the length of the probe 91 in the chordwise direction is a, the length of the entire brace 3 in the chordwise direction is b, and α = b/a is defined. Since probe 92 is relatively small, the magnitude of α is considered to determine the overall chordal length of probe 9. The value of alpha cannot be too large, otherwise the force bearing function of the support plate 3 is easily influenced; and the value of alpha is preferably 0.15-0.3, otherwise, the low-speed airflow effect of the adsorbed boundary layer is poor. The length ratio beta in the spanwise direction is defined as the ratio of the height of the probe 91 in the spanwise direction to the height of the support plate 3 in the spanwise direction, and the value range of beta is preferably 0.2-0.8.
In the design or experiment stage, the values of alpha and beta are adjusted in a combined manner, so that the test value obtained by measuring the probe is in the range of the design requirement. For example, by a numerical simulation or test method, the distribution form of the airflow section at the outlet of the support plate is inspected until the distribution of the inlet parameters of the high-pressure compressor falls within the deviation range allowed by the design requirement, and then the design can be completed. The deviation range of the probe 9 from the actual value is required to be within plus or minus 0.5% of the design requirement.
Fig. 5 shows a graph of the test results of the test, with the ordinate Y representing the proportion of the radial height of the plate 3 in the spanwise direction, e.g. Y =0.1 representing the position at 10% of the radial height of the plate 3. The abscissa X represents the ratio of the pressure value measured by the probe 9 at the point to the average pressure value of the outlet section of the support plate. The solid line A is the design requirement value of the section airflow parameter, and the dotted lines E' and E are respectively the plus and minus 0.5% deviation lines of the design requirement value.
In the first embodiment, as shown in point B in fig. 5, when the probe geometric parameters are α =0.3 and β =0.8, the probe 91 is located at 80% of the span-wise direction of the support plate, the chord-wise length is 30% of the support plate, and the pressure value measured by using the above-mentioned detection device is shown in point B in fig. 5, and the measurement result B falls within the tolerance band of the design requirement, that is, the ratio of the measurement result of the probe to the average pressure value of the outlet section of the support plate satisfies the design requirement.
In the second embodiment, as shown by point C in fig. 5, when the probe geometric parameters α =0.15 and β =0.56, the probe 91 is located at 56% of the span-wise direction of the support plate, the chord-wise length is 15% of the support plate, and the pressure value measured by using the above-mentioned detection device is shown by point C in fig. 5, and the measurement result C falls within the tolerance band of the design requirement, which meets the design requirement.
In the third embodiment, as shown by point D in fig. 5, when the probe geometric parameters are α =0.19 and β =0.24, the probe 91 is located at 24% of the span-wise direction of the support plate, the chord-wise length is 19% of the support plate, and the pressure value measured by using the above-mentioned detection device is shown by point D in fig. 5, and the measurement result D falls within the tolerance band of the design requirement, so as to meet the design requirement.
In addition, the parameter values can be adjusted in the parameter range, and probes at other positions can be arranged, so long as the measurement result falls within the design requirement range, the design requirement can be met.
In connection with the above description of the detection device, it is also understood that a strip is provided, which comprises a bleed air channel and a flow channel, in order to eliminate low-velocity gas vortices 50 at the trailing edge of the strip. The air-entraining channel is positioned inside the support plate and is used for entraining air to the outside of the air compressor. The opening of the flow channel is positioned at the tail edge of the support plate and extends from the tail edge to the front edge, and the flow channel is communicated with the bleed air channel.
When the low-speed airflow vortex 50 is formed at the tail edge of the support plate, high-pressure airflow is formed at the flow channel, and the low-speed airflow at the tail edge of the support plate can be effectively eliminated by utilizing a differential pressure airflow channel formed by the high-pressure airflow at the position and the low-pressure airflow outside the support plate, so that the airflow loss is reduced, and the overall performance of the compressor is improved.
In one embodiment, the flow channel is a hole structure or a slit structure formed on the support plate, and the hole structure or the slit structure can construct a gas flow channel so as to introduce gas to form a gas flow channel. In another embodiment, the flow channel may be defined by a groove in the strip and an external probe.
In one embodiment, the flow channel extends along the chord direction of the support plate, and the ratio alpha of the length of the flow channel in the chord direction to the length of the support plate in the chord direction is in the range of 0.15-0.3, so that a certain path of gas flow channel is provided, low-speed gas flow at the tail edge of the support plate is guided conveniently, and accumulation of the low-speed gas flow is eliminated. The length ratio α is defined by referring to the previous embodiments, and is not described herein.
In combination with the introduction of the support plate, a compressor can be understood, the compressor comprises a high-pressure compressor and a low-pressure compressor, and the support plate is used for connecting the high-pressure compressor and the low-pressure compressor, so that the support plate has a force bearing effect and can eliminate tail edge airflow, thereby reducing airflow loss and improving the overall performance of the compressor.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. For example, the probe embedded in the support plate may also be a probe for detecting other gas flow parameters such as temperature or gas content. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (5)
1. A detection device arranged in the compressor, which is characterized in that,
comprises a support plate and a probe;
the support plate comprises a groove and an air entraining channel, the groove is arranged at the tail edge of the support plate and extends from the tail edge to the front edge, and the air entraining channel is used for entraining air to the outside of the compressor;
the probe comprises a probe body and a probe body, the probe body is embedded into the groove, a flow channel is limited by the probe body and the groove, the flow channel is communicated with the air entraining channel, and the probe is positioned outside the support plate.
2. The probe apparatus of claim 1, wherein the probe body is fixedly connected to the groove surface of the groove in a span-wise direction or a thickness direction of the strip.
3. A probe device as claimed in claim 2 wherein the probe body is integrally formed with the support plate.
4. The probe apparatus of claim 1, wherein the groove extends along a chordwise direction and a spanwise direction of the support plate, a ratio α of a length of the probe body in the chordwise direction to the length of the support plate in the chordwise direction is in a range of 0.15 to 0.3, and a ratio β of the length of the probe body in the spanwise direction to the length of the support plate in the spanwise direction is in a range of 0.2 to 0.8.
5. A compressor comprising a high-pressure compressor and a low-pressure compressor, characterized in that a detection device according to any one of claims 1 to 4 is arranged between the high-pressure compressor and the low-pressure compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110978957.3A CN113417883B (en) | 2021-08-25 | 2021-08-25 | Detection device and air compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110978957.3A CN113417883B (en) | 2021-08-25 | 2021-08-25 | Detection device and air compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113417883A CN113417883A (en) | 2021-09-21 |
| CN113417883B true CN113417883B (en) | 2022-02-01 |
Family
ID=77719892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110978957.3A Active CN113417883B (en) | 2021-08-25 | 2021-08-25 | Detection device and air compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113417883B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113898609A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Engine air entraining flow channel and air entraining structure thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105715574A (en) * | 2014-12-05 | 2016-06-29 | 上海电气集团股份有限公司 | Vane regulation control device |
| CN109141900A (en) * | 2018-07-25 | 2019-01-04 | 中国航发沈阳发动机研究所 | A kind of probe measuring rotor outlet air-flow angle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6231301B1 (en) * | 1998-12-10 | 2001-05-15 | United Technologies Corporation | Casing treatment for a fluid compressor |
| FR2975451B1 (en) * | 2011-05-16 | 2016-07-01 | Turbomeca | PROCESS FOR BLOWING IN GAS TURBINE DIFFUSER AND CORRESPONDING DIFFUSER |
| BE1024605B1 (en) * | 2016-09-27 | 2018-04-26 | Safran Aero Boosters S.A. | CARTRIDGE WITH SUCTION ARMS FOR AXIAL TURBOMACHINE |
| US11015453B2 (en) * | 2017-11-22 | 2021-05-25 | General Electric Company | Engine component with non-diffusing section |
| US10738645B2 (en) * | 2018-08-31 | 2020-08-11 | Raytheon Technologies Corporation | Embedded triaxial epoxy cap probe |
-
2021
- 2021-08-25 CN CN202110978957.3A patent/CN113417883B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105715574A (en) * | 2014-12-05 | 2016-06-29 | 上海电气集团股份有限公司 | Vane regulation control device |
| CN109141900A (en) * | 2018-07-25 | 2019-01-04 | 中国航发沈阳发动机研究所 | A kind of probe measuring rotor outlet air-flow angle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113417883A (en) | 2021-09-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0186609B1 (en) | Temperature probe | |
| Schulz et al. | Three-dimensional separated flow field in the endwall region of an annular compressor cascade in the presence of rotor-stator interaction: Part 2—unsteady flow and pressure field | |
| CA2710009A1 (en) | Fan stall detection system | |
| Sareen et al. | Effects of leading-edge protection tape on wind turbine blade performance | |
| CN113417883B (en) | Detection device and air compressor | |
| Rolfes et al. | Experimental investigation of circumferential groove casing treatments for large tip clearances in a low speed axial research compressor | |
| CN110043370B (en) | Air flow measuring method of turbofan engine core machine | |
| EP3620630B1 (en) | Method and system for separated flow detection | |
| Walker et al. | Periodic transition on an axial compressor stator: Incidence and clocking effects: Part I—Experimental data | |
| Bae et al. | Active control of tip clearance flow in axial compressors | |
| Kato et al. | Experimental and numerical investigation on compressor cascade flows with tip clearance at a low Reynolds number condition | |
| Barker et al. | Influence of compressor exit conditions on combustor annular diffusers, part 1: diffuser performance | |
| WO2016170114A1 (en) | Measuring total pressure of a fluid in a turbomachine | |
| Zierke et al. | Measurement and analysis of total-pressure unsteadiness data from an axial-flow compressor stage | |
| EP4177442A1 (en) | Air inlet strut for aircraft engine | |
| Layachi et al. | Effect of the axial spacing between rotor and stator with regard to the indexing in an axial compressor | |
| Wartzek et al. | Realistic inlet distortion patterns interacting with a transonic compressor stage | |
| Zeschky et al. | Effects of stator wakes and spanwise nonuniform inlet conditions on the rotor flow of an axial turbine stage | |
| JPH08326555A (en) | Gas turbine for pressurized fluidized bed combustion plant and method for detecting secular deterioration of turbine | |
| Gostelow et al. | Performance comparisons of high Mach number compressor rotor blading | |
| Satta et al. | Wake control by boundary layer suction applied to a high-lift low-pressure turbine blade | |
| Hoheisel et al. | Influence of free stream turbulence and blade pressure gradient on boundary layer and loss behaviour of turbine cascades | |
| Mailach et al. | Wake-induced boundary layer transition in a low-speed axial compressor | |
| Yamamoto et al. | Unsteady endwall/tip-clearance flows and losses due to turbine rotor-stator interaction | |
| Walker et al. | Periodic Transition on an Axial Compressor Stator—Incidence and Clocking Effects: Part I—Experimental Data |
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 |