CN111577664A - Stator blade pressure pulsation measuring device - Google Patents
Stator blade pressure pulsation measuring device Download PDFInfo
- Publication number
- CN111577664A CN111577664A CN202010409257.8A CN202010409257A CN111577664A CN 111577664 A CN111577664 A CN 111577664A CN 202010409257 A CN202010409257 A CN 202010409257A CN 111577664 A CN111577664 A CN 111577664A
- Authority
- CN
- China
- Prior art keywords
- blade
- pressure pulsation
- film sensor
- measuring device
- pvdf
- 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
- 230000010349 pulsation Effects 0.000 title claims abstract description 30
- 239000002033 PVDF binder Substances 0.000 claims abstract description 62
- 229920002981 polyvinylidene fluoride Polymers 0.000 claims abstract description 62
- 238000012360 testing method Methods 0.000 claims abstract description 19
- 238000005259 measurement Methods 0.000 claims abstract description 12
- 239000010408 film Substances 0.000 claims description 39
- 239000010410 layer Substances 0.000 claims description 28
- 239000010409 thin film Substances 0.000 claims description 22
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 20
- 229910052782 aluminium Inorganic materials 0.000 claims description 20
- 238000003491 array Methods 0.000 claims description 6
- 239000011241 protective layer Substances 0.000 claims description 6
- 238000010008 shearing Methods 0.000 claims description 5
- 239000003292 glue Substances 0.000 claims description 4
- 239000000565 sealant Substances 0.000 claims description 3
- 238000004026 adhesive bonding Methods 0.000 claims description 2
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims 1
- 239000012790 adhesive layer Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 230000037303 wrinkles Effects 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
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- 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
- 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
- F04D29/646—Mounting or removal of fans
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
- G01L1/16—Measuring force or stress, in general using properties of piezoelectric devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The application belongs to the technical field of aviation turbofan engine fan noise measurement, in particular to stator blade pressure pulsation measuring device includes: the blade base body is provided with an upper edge plate, a lower edge plate and a blade part, wherein a blade basin and/or a blade back of the blade part are/is provided with a thinning area, and in addition, the upper edge plate is provided with a lead groove; the PVDF piezoelectric film sensor is laid in the thinning area; one end of the test lead penetrates through the lead slot and is connected with the PVDF piezoelectric film sensor on the corresponding side; and the data collector is connected to the other end of the test lead through a charge amplifier or a current amplifier. The stator blade pressure pulsation measuring device has the advantages that the blades are easy to install, the spatial resolution is higher, the influence on the flow field is small, and the number of the sensors which can be arranged in the array coverage area and the space is superior to that of the existing measuring system.
Description
Technical Field
The application belongs to the technical field of aviation turbofan engine fan noise measurement, and particularly relates to a stator blade pressure pulsation measuring device.
Background
Modern aviation turbofan engines with large bypass ratio generally comprise a fan, a booster stage, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine, wherein fan noise becomes one of the main noise sources of civil aircrafts, and rotating and static interference noise is the main component of the fan noise.
The main source of the rotor/stator interference noise is unsteady pressure pulsation generated when a wake impacts a stator blade when the rotor rotates, and the coupling relation between the rotor/stator interference noise is clarified through the surface pressure pulsation of the blade, so that the rotor/stator interference noise has important significance for improving the noise of the fan. Although the unsteady pressure pulsation distribution of the surface of the stator blade under the impact of the rotor wake can be obtained by means of theoretical analysis or numerical simulation and the like, the pressure pulsation of the blade still needs to be measured from the angle of a test, the accuracy of the theoretical analysis or the numerical simulation is verified, the noise reduction effect of the low-noise design is confirmed, and a complete low-noise design and verification flow is formed.
At present, a measurement technology based on a pressure sensor is adopted, but the installation of the used dynamic pressure sensors such as Kulite and the like needs to destroy the blade structure, so that the actual distribution of a flow field can be influenced, and the sensors are limited by space, so that the number of the arranged sensors is very limited, and the pressure field of the whole blade cannot be effectively described.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a stator vane pressure pulsation measuring apparatus.
The application discloses stator blade pressure pulsation measuring device includes:
the blade comprises a blade base body and a blade base body, wherein the blade base body is provided with an upper edge plate, a lower edge plate and a blade part positioned between the upper edge plate and the lower edge plate, a blade basin and/or a blade back of the blade part are/is concavely provided with a thinning area with a preset outer contour shape and thickness, and in addition, a lead groove is formed in the side surface, corresponding to the blade basin and/or the blade back, of the upper edge plate;
the outer contour shape of the PVDF piezoelectric film sensor is similar to that of a thinning area of the leaf basin and/or the leaf back, the thickness of the PVDF piezoelectric film sensor is smaller than that of the thinning area, and the PVDF piezoelectric film sensor is paved in the thinning area;
one end of the test lead penetrates through a lead slot on the upper edge plate and then is connected with the PVDF piezoelectric film sensor on the corresponding side;
and the data collector is connected to the other end of the test lead through a charge amplifier or a current amplifier.
According to at least one embodiment of the present application, the PVDF piezoelectric thin film sensor comprises an upper aluminum electrode layer, a lower aluminum electrode layer and a PVDF thin film positioned between the upper aluminum electrode layer and the lower aluminum electrode layer, wherein a measuring point is arranged in the PVDF thin film, and wherein
And one end of the test lead is respectively connected to the upper and lower aluminum electrode layers.
According to at least one embodiment of the application, the number of the measuring points is multiple, the measuring points are arranged on the PVDF film in a longitudinal and transverse array mode, the overall outline is similar to that of the thinning area, and the measuring points are arranged on the PVDF film in a longitudinal and transverse array mode, wherein the measuring points are arranged on the PVDF film in a longitudinal and transverse array mode, the overall outline of the PVDF film is similar to
A first preset distance is reserved between any two adjacent measuring points in the same longitudinal queue, a second preset distance is reserved between any two adjacent measuring points in the same transverse queue, and a third preset distance is reserved between the edges of the thin-shearing areas corresponding to the distance between the measuring points on the outermost side in the longitudinal and transverse arrays; and
and in the plane direction of the thinning area, the test lead has a fourth preset distance from two side edges of the lead groove.
According to at least one embodiment of the present application, the first predetermined pitch is 7 mm; the second predetermined spacing is 15 mm; the third predetermined spacing is 5 mm; the fourth predetermined spacing is 1 mm.
According to at least one embodiment of the application, the blade base body and the upper edge plate are of a split structure and are connected through bolt holes and matched bolts.
According to at least one embodiment of the application, the PVDF piezoelectric film sensor is fixedly laid in the thinning area through gluing, and in addition, a sealant is laid in a gap between the outermost measuring point in the longitudinal and transverse arrays and the edge of the thinning area.
According to at least one embodiment of the application, the thickness of a glue layer between the PVDF piezoelectric thin film sensor and the thin shearing area is 0.05-0.2 mm, and the 180-degree peeling strength of the glue layer is 30-50N/cm.
According to at least one embodiment of the application, the outer sides of the upper aluminum electrode layer and the lower aluminum electrode layer of the PVDF piezoelectric film sensor are further provided with a protective layer or a shielding layer.
According to at least one embodiment of the present application, the thickness of the outer surfaces of the upper and lower aluminum electrode layers or the outer surfaces of the protective layers or the outer surfaces of the shield layers of the PVDF piezoelectric thin film sensor is the same as the thickness of the outer surfaces of the blade portions.
According to at least one embodiment of the present application, the PVDF piezoelectric thin film sensor operates in a thickness mode, the stress in both the length direction and the width direction becomes 0, and the piezoelectric equation is:
D3＝d33×F/lw
wherein d is33Is the piezoelectric constant in the thickness direction, F is the applied external force, l is the length of the PVDF piezoelectric thin film sensor, and w is the width of the PVDF piezoelectric thin film sensor.
The application has at least the following beneficial technical effects:
the stator blade pressure pulsation measuring device has the advantages that the blades are easy to install, the spatial resolution is higher, the influence on the flow field is small, and the number of the sensors which can be arranged in the array coverage area and the space is superior to that of the existing measuring system.
Drawings
FIG. 1 is a schematic structural diagram of a stator vane pressure pulsation measurement apparatus according to the present application;
FIG. 2 is a schematic structural diagram of a blade substrate in the stator blade pressure pulsation measurement apparatus of the present application;
FIG. 3 is a schematic cross-sectional view B-B of FIG. 2;
FIG. 4 is a schematic cross-sectional structure diagram of a PVDF piezoelectric film sensor in the stator blade pressure pulsation measurement device of the present application;
FIG. 5 is a schematic view of the arrangement of the measuring points in the stator blade pressure pulsation measuring apparatus of the present application;
FIG. 6 is a schematic view of the arrangement of the test leads in the stator vane pressure pulsation measurement apparatus of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be understood that some terms of art that may be referred to in the description of the present application, such as "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," etc., indicate orientations and positional relationships that are based on the orientation shown in the drawings and are used merely for convenience in describing the present application and to simplify the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated without thereby limiting the scope of the present application.
The stator vane pressure pulsation measurement apparatus of the present application will be described in further detail with reference to fig. 1 to 6.
The application discloses stator blade pressure pulsation measuring device, as shown in fig. 1, can include parts such as blade base member 1, PVDF piezoelectric film sensor 2, test lead 3 and data collection station 5.
Specifically, as shown in fig. 2, the blade base 1 is preferably a straight blade, and has an upper edge plate 11, a lower edge plate 12, and a blade portion 13 located between the upper edge plate 11 and the lower edge plate 12; a thinning region 131 with a predetermined outer contour shape and thickness is concavely provided on a blade basin (not shown on the back side of fig. 2) and/or a blade back (shown in a schematic view of the blade back in fig. 2) of the blade portion 13, and a lead groove 111 is opened on a side surface of the upper flange 11 corresponding to the blade basin and/or the blade back.
It should be noted that the predetermined outer contour shape and thickness of the thinning-out region 131 can be appropriately selected according to specific needs, so as to mainly ensure that the thinned blade substrate 1 meets the strength requirement; in addition, the thinned region 131 may be opened by a tool at a later stage, or may be formed integrally with the blade base 1 at an early stage of the processing of the blade base 1.
Further, in this embodiment, it is preferable that the blade base 1 and the upper edge plate 11 are of a split structure, a threaded hole 112 is formed through the top of the upper edge plate 11 in a direction toward the blade base 1, and a matching threaded counter bore is formed in the top of the blade base 1, so that the blade base 1 and the upper edge plate 11 are connected by a bolt.
As shown in fig. 1, the PVDF piezoelectric thin film sensor 2 has an outer contour shape similar to that of the thinning-out region 131 of the leaf pot and/or leaf back, has a thickness smaller than that of the thinning-out region 131 (in this embodiment, it is preferable that the total thickness of the PVDF piezoelectric thin film sensor is about 1mm), and is laid in the thinning-out region 131.
The sensor is manufactured by utilizing the unique piezoelectric integral characteristic of a PVDF film, and the PVDF is used for measuring the blade; the PVDF piezoelectric film sensor 2 works in a thickness mode, the piezoelectric film deforms in the thickness direction under the action of a loading force, the stress in the length direction and the stress in the width direction of the piezoelectric film both become 0, and the piezoelectric equation is as follows:
D3＝d33×F/lw
wherein d is33Is the piezoelectric constant in the thickness direction, F is the applied external force, l is the length of the PVDF piezoelectric thin film sensor, and w is the width of the PVDF piezoelectric thin film sensor.
As shown in fig. 6, in the present embodiment, the overall outer contour size of the PVDF piezoelectric thin film sensor 2 is preferably slightly smaller than the outer contour size of the shear thinning region 131. Further, the PVDF piezoelectric film sensor 2 may adopt a currently known PVDF piezoelectric film sensor, and in this embodiment, as shown in fig. 4 and 5, it is preferable that the PVDF piezoelectric film sensor 2 includes an upper aluminum electrode layer 21, a lower aluminum electrode layer 21, and a PVDF film 22 located between the upper aluminum electrode layer 21 and the lower aluminum electrode layer 21, and the measurement point 221 is provided in the PVDF film 22.
Further, the PVDF film 22 is in the same shape as the thinning-out region 131 and is slightly smaller in size than the thinning-out region; after the PVDF piezoelectric film sensor 2 is paved, the surface of the PVDF film 22 is smooth, wrinkles and bubbles are not allowed, local bulges are not allowed to exist, the outer surface of the PVDF film is the required blade profile of the blade after the PVDF film sensor is fixed, and the thickness and the oversize of the outer surface are the same as those of the blade matrix 1; in addition, the number and the arrangement position of the measuring points 221 on the PVDF film 22 can be selected as needed, in this embodiment, as shown in fig. 5, preferably, the number of the measuring points 221 is multiple, the multiple measuring points 221 are arranged in a vertical and horizontal array on the PVDF film 22, and the overall outer contour is similar to the outer contour of the thinned region 131. Wherein the transverse direction is along the flow line direction, and all the measuring points should be covered by the PVDF film 22.
In addition, due to the fact that the measuring points are arranged in a large number, in order to guarantee sensitivity and accuracy, a first preset distance is reserved between any two adjacent measuring points 221 in the same longitudinal queue, a second preset distance is reserved between any two adjacent measuring points 221 in the same transverse queue, and in addition, a third preset distance is reserved between the outermost measuring point 221 in the longitudinal and transverse arrays and the edge of the corresponding thinning area 131. Similarly, the sizes of the predetermined intervals may be selected as needed, and in this embodiment, the first predetermined interval is preferably 7 mm; the second predetermined spacing is 15 mm; the third predetermined pitch is 5 mm.
Further, in this embodiment, preferably, the PVDF piezoelectric thin film sensor 2 is fixedly laid in the thinning-shearing region 131 by an adhesive method, the adhesive between the PVDF piezoelectric thin film sensor 2 and the thinning-shearing region 131 forms an adhesive layer, the thickness of the adhesive layer is 0.05-0.2 mm, and the 180 ° peel strength of the adhesive layer is 30-50N/cm.
Further, it is preferable to lay a sealant in the gap between the outermost (i.e. all the measuring points 221 around the periphery) and the edge (including the upper and lower edges, the left and right edges) of the thinned region 131 in the vertical and horizontal arrays.
Further, in another embodiment, it is preferable that a protective layer or a shielding layer is further provided outside the upper and lower aluminum electrode layers 21 of the PVDF piezoelectric thin film sensor 2, and the thickness of the outer surfaces of the upper and lower aluminum electrode layers 21 of the PVDF piezoelectric thin film sensor 2, the outer surfaces of the protective layer, or the outer surfaces of the shielding layer is preferably the same as the thickness of the outer surface of the blade 13.
As shown in fig. 1 and 6, one end of the test lead 3 penetrates through the lead groove 111 on the upper edge plate 11 and is connected to the PVDF piezoelectric film sensor 2 on the corresponding side, and in this embodiment, the test lead 3 is preferably a flat wire, and the thickness is not greater than 1 mm; further, one end of the test lead 3 is connected to the upper and lower aluminum electrode layers 21 of the PVDF piezoelectric thin film sensor 2.
In addition, as shown in fig. 6, in the present embodiment, it is preferable that the test lead 3 has a fourth predetermined pitch from both left and right side edges of the lead groove 111 in the plane direction (left and right direction in fig. 6) of the thinned region 131; the size of the fourth predetermined interval can be selected as needed, and in this embodiment, the fourth predetermined interval is preferably 1 mm.
As shown in fig. 1, a data collector 5 is connected to the other end of the test lead 3 through a charge amplifier 4 or a current amplifier. The data collector 5 and the charge amplifier 4 or the current amplifier form a front-end circuit, and the test lead 3 is led out through the lead slot 111 and then connected with the front-end circuit to form a measurement system; in addition, the charge amplifier 4 or the current amplifier plays a crucial role in the whole front-end circuit, and the performance of the charge amplifier or the current amplifier is most directly influenced on the signal acquisition.
To sum up, the stator blade pressure pulsation measuring device of this application, the blade is easily installed, and spatial resolution is higher, and is little to the flow field influence, and array coverage area and space can arrange sensor figure and all are superior to current measurement system.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A stator vane pressure pulsation measurement device, comprising:
the blade base body (1) is provided with an upper edge plate (11), a lower edge plate (12) and a blade part (13) positioned between the upper edge plate (11) and the lower edge plate (12), a blade basin and/or a blade back of the blade part (13) are/is concavely provided with a shearing thin area (131) with a preset outer contour shape and thickness, and in addition, a lead wire groove (111) is formed in the side surface, corresponding to the blade basin and/or the blade back, of the upper edge plate (11);
the PVDF piezoelectric thin film sensor (2) is similar to the outer contour shape of a thinning area (131) of the leaf basin and/or the leaf back, is smaller than the thickness of the thinning area (131), and is paved in the thinning area (131);
one end of the test lead (3) penetrates through a lead slot (111) in the upper edge plate (11) and then is connected with the PVDF piezoelectric film sensor (2) on the corresponding side;
and the data collector (5) is connected to the other end of the test lead (3) through a charge amplifier (4) or a current amplifier.
2. The stator blade pressure pulsation measuring device according to claim 1, wherein the PVDF piezoelectric film sensor (2) comprises upper and lower aluminum electrode layers (21) and a PVDF film (22) between the upper and lower aluminum electrode layers (21), a measuring point (221) is provided in the PVDF film (22), wherein
One end of the test lead (3) is respectively connected to the upper and lower aluminum electrode layers (21).
3. The stator blade pressure pulsation measuring device according to claim 2, wherein the number of the measuring points (221) is multiple, the multiple measuring points (221) are arranged on the PVDF film (22) in a criss-cross array, the overall outer contour is similar to that of the shear thinning region (131), and the outer contour of the whole measuring points is similar to that of the shear thinning region (131), wherein
A first preset interval is reserved between any two adjacent measuring points (221) in the same longitudinal queue, a second preset interval is reserved between any two adjacent measuring points (221) in the same transverse queue, and a third preset interval is reserved between the edges of the thinning area (131) corresponding to the distance between the measuring points (221) on the outermost side in the longitudinal and transverse arrays; and
in the plane direction of the thinning area (131), the test leads (3) have a fourth preset distance from two side edges of the lead groove (111).
4. The stator vane pressure pulsation measuring device according to claim 3, wherein the first predetermined pitch is 7 mm; the second predetermined spacing is 15 mm; the third predetermined spacing is 5 mm; the fourth predetermined spacing is 1 mm.
5. The stator vane pressure pulsation measuring device according to claim 1, wherein the vane base body (1) and the upper edge plate (11) are of a split structure and are connected by bolt holes (112) therethrough and adapted bolts.
6. The stator blade pressure pulsation measuring device according to claim 3, wherein the PVDF piezoelectric film sensor (2) is fixedly laid in the shear thinning region (131) by means of gluing, and further, a sealant is laid in a gap between the outermost measuring point (221) in the longitudinal and transverse arrays and the edge of the shear thinning region (131).
7. The stator blade pressure pulsation measuring device according to claim 6, wherein the thickness of the glue line between the PVDF piezoelectric thin film sensor (2) and the shear thinning zone (131) is 0.05-0.2 mm, and the 180 DEG peel strength of the glue line is 30-50N/cm.
8. The stator blade pressure pulsation measuring device according to claim 2, wherein a protective layer or a shielding layer is further provided outside the upper and lower aluminum electrode layers (21) of the PVDF piezoelectric film sensor (2).
9. The stator blade pressure pulsation measuring device according to claim 8, wherein the thickness of the outer surfaces of the upper and lower aluminum electrode layers (21) or the outer surfaces of the protective layers or the outer surfaces of the shield layers of the PVDF piezoelectric film sensor (2) is the same as the thickness of the outer surfaces of the blade portions (13).
10. The stator blade pressure pulsation measuring device according to claim 8, wherein the PVDF piezoelectric film sensor (2) operates in a thickness mode, the stress in both the length direction and the width direction thereof becomes 0, and the piezoelectric equation is:
D3＝d33×F/lw
wherein d is33Is the piezoelectric constant in the thickness direction, F is the applied external force, l is the length of the PVDF piezoelectric thin film sensor, and w is the width of the PVDF piezoelectric thin film sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010409257.8A CN111577664A (en) | 2020-05-14 | 2020-05-14 | Stator blade pressure pulsation measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010409257.8A CN111577664A (en) | 2020-05-14 | 2020-05-14 | Stator blade pressure pulsation measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111577664A true CN111577664A (en) | 2020-08-25 |
Family
ID=72122998
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010409257.8A Pending CN111577664A (en) | 2020-05-14 | 2020-05-14 | Stator blade pressure pulsation measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111577664A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412953A (en) * | 2021-12-24 | 2022-04-29 | 南京航空航天大学 | Helicopter rotor piezoelectric film vibration suppression structure and method based on passive control |
| CN114544136A (en) * | 2022-04-22 | 2022-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Embedded surface pressure gradient measuring device |
| CN115575081A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional lattice design method and device for wind tunnel pulsating pressure measurement |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1897423A (en) * | 2005-07-12 | 2007-01-17 | 株式会社电装 | Commutator motor |
| CN202100394U (en) * | 2011-06-15 | 2012-01-04 | 温州大学 | Wind turbine impeller with piezoelectric transducer |
| US20160252420A1 (en) * | 2013-10-18 | 2016-09-01 | United Technologies Corporation | Method and assembly for inspecting engine component |
| CN106015029A (en) * | 2016-05-12 | 2016-10-12 | 江苏大学 | System and method for measuring surface pressure of pump impeller blade |
| US20160312703A1 (en) * | 2013-12-17 | 2016-10-27 | United Technologies Corporation | Adaptive turbomachine cooling system |
| CN106092493A (en) * | 2015-04-29 | 2016-11-09 | 上海交通大学 | A kind of compressor blade tip Flow Field Distribution real-time measurement apparatus and method |
-
2020
- 2020-05-14 CN CN202010409257.8A patent/CN111577664A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1897423A (en) * | 2005-07-12 | 2007-01-17 | 株式会社电装 | Commutator motor |
| CN202100394U (en) * | 2011-06-15 | 2012-01-04 | 温州大学 | Wind turbine impeller with piezoelectric transducer |
| US20160252420A1 (en) * | 2013-10-18 | 2016-09-01 | United Technologies Corporation | Method and assembly for inspecting engine component |
| US20160312703A1 (en) * | 2013-12-17 | 2016-10-27 | United Technologies Corporation | Adaptive turbomachine cooling system |
| CN106092493A (en) * | 2015-04-29 | 2016-11-09 | 上海交通大学 | A kind of compressor blade tip Flow Field Distribution real-time measurement apparatus and method |
| CN106015029A (en) * | 2016-05-12 | 2016-10-12 | 江苏大学 | System and method for measuring surface pressure of pump impeller blade |
Non-Patent Citations (1)
| Title |
|---|
| 胡骏 等: "动叶尾迹对静子非定常气动性能影响的研究", 《航空动力学报》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412953A (en) * | 2021-12-24 | 2022-04-29 | 南京航空航天大学 | Helicopter rotor piezoelectric film vibration suppression structure and method based on passive control |
| CN114544136A (en) * | 2022-04-22 | 2022-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Embedded surface pressure gradient measuring device |
| CN114544136B (en) * | 2022-04-22 | 2022-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Embedded surface pressure gradient measuring device |
| CN115575081A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional lattice design method and device for wind tunnel pulsating pressure measurement |
| CN115575081B (en) * | 2022-12-09 | 2023-03-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional lattice design method and device for wind tunnel pulsating pressure measurement |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111577664A (en) | Stator blade pressure pulsation measuring device | |
| US9429481B2 (en) | Apparatus and method for measuring total air temperature within an airflow | |
| Paterson et al. | Acoustic radiation and surface pressure characteristics of an airfoil due to incident turbulence | |
| Ganz et al. | Boeing 18-inch fan rig broadband noise test | |
| Murayama et al. | Experimental study on slat noise from 30P30N three-element high-lift airfoil at JAXA hard-wall lowspeed wind tunnel | |
| EP2159559B1 (en) | Resistive contact sensors for large blade and airfoil pressure measurements | |
| Murayama et al. | Experimental study of slat noise from 30P30N three-element high-lift airfoil in JAXA kevlar-wall low-speed wind tunnel | |
| CN101672247A (en) | Method and arrangement to adjust the pitch of wind turbine blades | |
| CN104897275A (en) | Engine noise testing method based on outfield airplane | |
| Oerlemans et al. | Acoustic array measurements of a 1: 10.6 scaled Airbus A340 model | |
| CN213932415U (en) | Ultrasonic icing detection wing type test device | |
| CN115575081A (en) | Two-dimensional lattice design method and device for wind tunnel pulsating pressure measurement | |
| CN115384780A (en) | Skin temperature measurement structure and manufacturing method thereof | |
| Davy et al. | Aeroacoustic Behaviour of a 1: 11 Scale Airbus Model in the Open Anechoic Wind Tunnel CEPRA 19 | |
| Moriarty | Development and validation of a semi-empirical wind turbine aeroacoustic code | |
| CN112781825A (en) | Suction structure for improving flow field quality of plane cascade wind tunnel and design method thereof | |
| CN106247940A (en) | A kind of measuring method measuring molded line three-dimensional position at quarter | |
| CN115307811B (en) | Blade tip leakage flow testing method based on wall surface static pressure | |
| Lorber | Blade‐Vortex Interaction Data Obtained from a Pressure‐Instrumented Model UH‐60A Rotor at the DNW | |
| CN112097628B (en) | Method for measuring radial clearance of turbine blade top, capacitance sensor and storage medium | |
| CN213331682U (en) | Flow guide ring assembly | |
| CN114910273A (en) | Aeroengine sound source testing device, core machine and sound source testing method | |
| EP4230865A1 (en) | Anti-lightning system for wind turbine blade, wind power generation facility, and method of monitoring wind turbine blade | |
| EP3073241A1 (en) | Analyzing the boundary layer of a rotor blade | |
| CN115876428A (en) | Transonic speed continuous wind tunnel wall pressure measuring device |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200825 |