CN114166478A - Measuring device - Google Patents
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- CN114166478A CN114166478A CN202111223581.1A CN202111223581A CN114166478A CN 114166478 A CN114166478 A CN 114166478A CN 202111223581 A CN202111223581 A CN 202111223581A CN 114166478 A CN114166478 A CN 114166478A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0075—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by means of external apparatus, e.g. test benches or portable test systems
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a measuring device, belongs to the technical field of engine sealing part testing devices, and solves the technical problem of fingertip or brush type sealing rigidity rate and hysteresis rate measurement. Including the base and with base sealing connection's end cover, install the sealed runway that thrust unit and loop configuration set up in the base, it establishes to be surveyed the piece cover sealed runway, and sealed runway circumference is predetermine the position and is set up the opening of predetermineeing quantity, the opening is used for sealed runway's gas tightness to when filling into the gas of predetermineeing pressure in the closed area that base and end cover formed, surveyed piece and/or sealed runway will closed area divide into high pressure side and low pressure side, through thrust unit acts on the different thrust of sealed runway, just sealed runway or surveyed the piece with the relative displacement that the base produced to accomplish the measurement of the sealed rigidification rate and the hysteresis rate of surveyed the piece. The invention aims to measure the rigidization rate and the hysteresis rate on a quasi side.
Description
Technical Field
The invention belongs to the technical field of engine sealing part testing, and particularly relates to a measuring device.
Background
A long life, low leakage rate fingertip seal of practical value is very beneficial for improving gas turbine engine component performance and engine thrust. The most direct value of finger tip seals and brush seals is to replace the labyrinth seal in high differential pressure areas of the engine. Compared with a comb tooth type seal, the fingertip seal can reduce 1-2% of air leakage of the engine, the fingertip seal is only used at the outlet of a high-pressure compressor of the engine, the fuel consumption (SFC) of the engine is expected to be reduced by 0.7-1.4%, and the direct use cost (DOC) is reduced by 0.3-0.7%. Tests prove that the novel flexible seals such as fingertip seals and brush seals have lower leakage rate than the labyrinth seals and have lower power loss than the labyrinth seals and the circumferential graphite seals.
The use condition, the service life and the sealing performance of the fingertip seal are directly related to the contact rigidity of the fingertip sheet and the seal track in the working process. The larger the contact rigidity is, the larger the heat generation amount of the seal is, the more the abrasion is accelerated when the temperature exceeds the allowable friction temperature, and the service life of the fingertip seal is shortened. At the same time, the operating conditions of high temperature, high speed and high packing pressure differential will affect the maximum temperature of the working face. Therefore, the design work of the contact type fingertip seal always focuses on how to keep the contact rigidity of the fingertip pieces and the seal track at a proper value in the working process, so that the sealing performance is ensured, and meanwhile, the use condition and the service life of the fingertip seal are improved. However, the existing research on the contact rigidity of the fingertip seal mainly depends on simulation, and the validity of a simulation result is lack of experimental evaluation.
Due to the influence of a sealing structure, friction force, working environment and the like, the conventional fingertip seal has a hysteresis characteristic on sealing performance, namely, the sealing pressure difference is not changed, when the rotating speed of a sealing rotor enters a descending region from the highest point, the leakage flow coefficient of the fingertip seal does not return to the original position along a curve when the rotating speed rises, but rises to a relatively high position. With the increase of the applied pressure, the friction force is obviously increased, the finger body is prevented from freely moving in the radial direction, and the radial rigidity of the finger body is increased, so that the finger tip seal has a 'stiffening effect'.
The "stiffening effect" and "hysteresis effect" of a fingertip seal can severely affect the sealing performance of the fingertip seal. At present, the 'rigidization effect' and the 'hysteresis effect' are improved mainly by structural improvement, and the rigidization rate and the hysteresis rate of fingertip seals and brush seals are evaluated and measured by a method which is not effective in forming a system.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a measuring device, which solves the technical problem of how to measure the rigidification rate and the hysteresis rate of fingertip seals, brush seals and the like. The technical scheme of the scheme has a plurality of technical beneficial effects, which are described as follows:
the utility model provides a measuring device is applicable to the measurement of the sealed rigidification rate of quilt survey piece and hysteresis rate, including the base and with base sealing connection's end cover, install the sealed runway that thrust unit and loop configuration set up in the base, quilt survey the piece cover and establish sealed runway, just sealed runway circumference is predetermine the position and is set up opening or the incision of predetermineeing quantity, wherein:
when gas with preset pressure is filled into the closed area formed by the base and the end cover, the detected piece and/or the sealing track divides the closed area into a high-pressure side and a low-pressure side, different thrust forces act on the sealing track through the thrust device, and the sealing track or the detected piece and the base generate relative displacement so as to finish the measurement of the sealing rigidification rate and the hysteresis rate of the detected piece.
Secondly, a measuring method is provided, which is suitable for measuring the seal stiffness rate and the hysteresis rate of the measured piece, and the method comprises the following steps:
s801, arranging a sealing runway in a sealing area, wherein the sealing runway is sleeved by the tested piece, and the outer surface of the tested piece abuts against the sealing area; a friction piece made of flexible materials is filled in a circumferential part area of the sealing track; an opening or a gap is formed in a preset position of the sealing track, and a detected piece and/or the sealing track divide the sealing area into a high-pressure side and a low-pressure side when high-pressure gas is supplemented;
s802, when the sealing runway is not sleeved by the tested pieceObtaining a first force F of the sealing runway pushed by a thrust device to a specified or preset displacementycAnd, a second force F that moves the predetermined bit back to the initial positionhc；
S803, when the closed area is in a zero-pressure environment and the sealing runway is sleeved by the tested piece, acquiring a third force F of the sealing runway pushed by a thrust device to be appointed or preset to be displacedy0And, a fourth force F that moves the predetermined position back to the initial positionh0；
S804, under the preset high-pressure environment, when the pressure difference between the high-pressure side and the low-pressure side is a preset value, acquiring a fifth force F of the sealing runway pushed by a thrust device to be appointed or preset to displaceyiAnd, a sixth force F that moves the predetermined position back to the initial positionhi；
And S805, determining the seal rigidization rate and the hysteresis rate of the tested piece according to the force of the thrust device in different environments.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
the device of present case carries out the unilateral through thrust unit and promotes, and when high pressure environment test, the air leakage of high pressure side can be reduced to the opening on the sealed runway, accomplishes the test through the displacement volume of sealed runway. The device can evaluate the rigidity performance of the sealing device, and the evaluation result has a traction effect on the design, analysis and improvement of the fingertip seal and the brush seal, and can provide a test basis for the forward design of the fingertip seal and the brush seal.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a front cross-sectional view of the device of the present invention;
FIG. 2 is a schematic view of a sealing runway;
FIG. 3 is a schematic view of an opening formed in the sealing track;
FIG. 4 is an assembly view of a tested piece and a sealing track;
wherein, 1, a tested piece; 2. a base; 3. an end cap; 4. a thrust device; 5. a graphite ring; 6. sealing the runway; 7. an opening; 8. air leakage holes; 9. and (4) supporting the base.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. 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 invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than the number, shape and size of the components in practical implementation, and the type, quantity and proportion of the components in practical implementation can be changed freely, and the layout of the components can be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. 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 otherwise specified.
The measuring device shown in fig. 1 is suitable for measuring the seal stiffness and hysteresis of the object 1, and the object 1 may be a fingertip seal, a brush seal, a circumferential graphite seal, an end face graphite seal, or other sealing devices having the same function. The measuring device comprises a base 2 and an end cover 3 connected with the base 2 in a sealing mode, and a thrust device 4 and a sealing runway 6 arranged in an annular structure are installed in the base 2. The tested piece 1 is sleeved with a sealing runway 6, a preset number of openings 7 or notches are arranged at preset positions in the circumferential direction of the sealing runway 6, the openings 7 or notches are used for sealing the sealing runway 6 in an air-tight manner in a high-pressure environment, and the positions of the openings 7 or notches are symmetrically arranged on the sealing runway 6.
When gas with preset pressure is filled into a closed area formed by the base 2 and the end cover 3, the detected piece 1 and/or the sealing runway 6 divide the closed area into a high-pressure side and a low-pressure side, at the moment, when the sealing runway 6 is pushed to a specified displacement, the gas leakage from the high-pressure side to the low-pressure side can be reduced by the opening 7 or the notch, a gas shielding surface is formed through a gap of the opening 7 or the notch, for example, under the action force of one side of the thrust device 4, one side of the sealing runway 6 is stressed, the other side of the sealing runway 6 forms a gap with the detected piece 1, the gas leakage is prevented by arranging the opening 7 or the notch, the high-pressure side and the low-pressure side meet the preset pressure difference, the measurement of the test piece under the preset pressure difference condition is ensured, and the performance of the detected piece 1 under the real working environment of the engine is better simulated.
During testing, the thrust device 4 acts on the sealing track 6 with different thrusts, preferably, acts on one side, and when the sealing track 6 or the tested piece 1 and the base 2 generate relative displacement, the sealing rigidification rate and the hysteresis rate of the tested piece 1 are measured.
As shown in fig. 4, in an assembly diagram of the seal track 6 and the tested piece 1, a plurality of grooves are formed on the inner ring surface of the tested piece 1 in a brush seal mode in the prior art.
As an embodiment provided by the present disclosure, as shown in fig. 2 and 3, the opening 7 is a folded line and/or an arc, the arc is, for example, S-shaped, the folded line is, for example, Z-shaped, or a combination thereof, so as to form a region with narrow air tightness, and prevent air at the high pressure side from leaking to the low pressure side, so as to reduce pressure leakage at the high pressure side and the low pressure side of the tested piece 1 in the sealed region.
Furthermore, the hem shape is the zigzag and sets up along sealed runway 6 circumference, or, the opening 7 that the arc structure and hem shape formed, or, the opening 7 that the arc structure symmetry formed.
Measuring device chooses for use prior art's product can, for example, thrust device 4 includes telescopic link and pressure sensor, displacement measurement device, wherein: the pressure sensor measures the acting force of the telescopic rod acting on the sealing runway 6,
the displacement measuring device measures the displacement of the object 1 under the effect of the opening 7 or the cut.
As the embodiment provided by the scheme, the base 2 is arranged in an annular structure, and the outer surface of the tested piece 1 is abutted against the inner surface of the base 2.
Furthermore, a support table or a support seat 9 or a support frame, etc. is installed inside the base 2, and can bear the sealing runway 6, and the tested piece 1 may not bear the sealing runway 6, and the tested piece 1 is resisted on the inner side wall of the base 2 by the sealing runway 6.
In the above device, a groove is formed in the facing surface of the sealing track 6 and the base 2, and a flexible friction member is embedded or filled in the groove to reduce the friction force, for example, the flexible friction member is a square ring structure made of graphite material to reduce the friction force with the base 2, and has a circular ring with a rectangular cross section.
Examples
The sealing runway 6 is provided with a Z-shaped opening 7, when the designated displacement of the sealing runway 6 is 0, the Z-shaped opening 7 is closed, and when the designated displacement of the sealing runway 6 is more than 0, the Z-shaped opening 7 is opened. Fig. 3 is a schematic view showing the opening of the zigzag opening 7. The Z-shaped opening 7 can effectively reduce air leakage from the high-pressure cavity to the low-pressure cavity when the sealing runway 6 moves.
The graphite ring 5 is installed on the sealing runway 6, the Z-shaped opening 7 (the graphite ring 5) is also formed in the graphite ring 5, and the Z-shaped opening 7 (the graphite ring 5) in the graphite ring 5 and the Z-shaped opening 7 in the sealing runway 6 are circumferentially staggered during installation (see figure 4), so that air leakage is reduced. The graphite ring 5 is assembled with the sealing runway 6 in an interference fit mode. The sliding friction is reduced by the high roughness and flatness requirements of the matching surface of the graphite ring 5 and the measuring base 2. The amount of gas leakage can be measured via the leakage orifice 8, if necessary, with minor corrections made by software of the prior art.
On the other hand, the measuring method of the device is suitable for measuring the seal stiffness rate and the hysteresis rate of the measured piece, and comprises the following steps:
s801, arranging a sealing runway in the sealing area, sleeving a tested piece on the sealing runway, and enabling the outer surface of the tested piece to abut against the sealing area; a friction piece made of flexible materials is filled in the peripheral part area of the sealing runway; an opening or a gap is formed in a preset position of the sealing track, and a detected piece and/or the sealing track divide a sealed area into a high-pressure side and a low-pressure side when high-pressure gas is supplemented;
s802, when the sealing runway is not sleeved by the tested piece, acquiring a first force F of the sealing runway pushed by a thrust device to be appointed or preset to displaceycAnd, the preset bit moves back to push upSecond force F of the start positionhc；
S803, when the sealed area is in a zero-pressure environment and the tested piece of the sealed runway is sleeved, acquiring a third force F of the sealed runway, which is pushed by a thrust device to be appointed or preset to be displacedy0And, a fourth force F that moves the predetermined position back to the initial positionh0；
S804, under the preset high-pressure environment, when the pressure difference between the high-pressure side and the low-pressure side is a preset value, acquiring a fifth force F of the sealing runway pushed by the thrust device to be appointed or preset to displaceyiAnd, a sixth force F that moves the predetermined position back to the initial positionhi；
And S805, determining the seal rigidization rate and the hysteresis rate of the tested piece according to the force of the thrust device in different environments.
Specifically, the method for determining the seal stiffness rate and the hysteresis rate of the tested piece comprises the following steps:
determining the pressure stroke rigidity K of the tested sealing device according to the force of the thrust device under different environmentsyiReturn stiffness KhiAnd satisfies the following conditions:
Kyi＝(Fyi-Fyc)/D
Khi＝(Fhi-Fhc) D, wherein D is a preset displacement;
retardation rate sigmaiAnd a rate of rigidification δiRespectively satisfy:
σi＝(Kyi-Khi)/Kyi，δi＝Kyi/Kyo。
the concrete implementation steps of the measurement of the rigidification rate and the hysteresis rate of the tested sealing device are as follows:
the method comprises the following steps: the rigidity and hysteresis rate measuring device is calibrated, the tested sealing device is not installed, the radial displacement D from 0.2mm to 1mm (interval of 0.2mm) is applied to the sealing track by the displacement giving device, and meanwhile, the force Fyc required by the sealing track to move to the specified displacement is measured by the force measuring device and recorded. The displacement of the sealing track is reduced from 1mm to 0.2mm by the displacement setting device, and the force Fhc required by the sealing track to move to the specified displacement is measured by the force measuring device and recorded.
Step two: when the differential pressure is 0, a radial displacement D from 0.2mm to 1mm (the interval is 0.1mm-0.2mm) is applied to the sealing track by the displacement setting device, and the force F required by the sealing track to move to the specified displacement is measured by the force measuring devicey0And recording.
Step three: the displacement of the sealing track is reduced from 1mm to 0.2mm by a displacement setting device, and the force F required by the sealing track to move to the specified displacement is measured by a force measuring deviceh0And recording.
Step four: inputting high-pressure air into the measuring device, and when the sealing pressure difference is 0.1MPa, 0.2MPa, 0.3MPa, 0.4MPa and 0.5MPa (the sealing pressure difference is the pressure of the high-pressure side pressure and the low-pressure side pressure), sequentially completing the first step and the second step, and recording the corresponding stress F measured by the force measuring deviceyiAnd Fhi(i distinguishes the measurement results under different pressure difference conditions, i is 0 to represent the pressure difference of 0MPa, i is 1 to represent the pressure difference of 0.1MPa, and so on).
Step five: and (3) calculating the pressure stroke stiffness Kyi, the return stroke stiffness Khi, the hysteresis rate sigma i and the rigidification rate delta i of the tested sealing device, and calculating formulas (1) to (4). The calculation results are recorded in a record table (see table 1).
Kyi＝(Fyi-Fyc)/D·························(1)
Khi＝(Fhi-Fhc)/D························(2)
σi＝(Kyi-Khi)/Kyi························(3)
δi＝Kyi/Kyo···························(4)，
The following table records are used and,
the products provided by the present invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the invention without departing from the inventive concept, and those improvements and modifications also fall within the scope of the claims of the invention.
Claims (9)
1. The utility model provides a measuring device, is applicable to the measurement of the sealed rigidification rate of quilt survey piece and hysteresis rate, its characterized in that, including the base and with base sealing connection's end cover, install the sealed runway that thrust unit and loop configuration set up in the base, quilt survey the piece cover and establish sealed runway, just sealed runway circumference is preset the position and is set up the opening or the incision of presetting quantity, opening or incision are used for the gas tightness of sealed runway to seal tightly, wherein:
when gas with preset pressure is filled into the closed area formed by the base and the end cover, the detected piece and/or the sealing track divides the closed area into a high-pressure side and a low-pressure side, different thrust forces act on the sealing track through the thrust device, and the sealing track or the detected piece and the base generate relative displacement so as to finish the measurement of the sealing rigidification rate and the hysteresis rate of the detected piece.
2. The measuring device of claim 1, wherein the opening is polygonal and/or curved to reduce pressure leakage from the high pressure side and the low pressure side of the object within the enclosed area.
3. The measuring device according to claim 2, wherein the folded edge is zigzag and is circumferentially arranged along the sealing track, or the opening formed by the arc-shaped structure and the folded edge is formed by the arc-shaped structure, or the opening formed by the arc-shaped structure is symmetrically formed.
4. The measuring device of claim 1, wherein the thrust device comprises a telescoping rod and a pressure sensor, a displacement measuring device, wherein:
the pressure sensor measures the acting force of the telescopic rod acting on the sealing runway;
the displacement measuring device measures the displacement of the measured piece under the action of the opening or the cut.
5. The measuring device of claim 1, wherein the outer surface of the member to be measured abuts the inner surface of the base.
6. The measuring device according to claim 1, wherein a groove is arranged on the surface of the sealing track, which faces the base, and a flexible friction piece is embedded or filled in the groove.
7. The measuring device of claim 6, wherein the flexible friction member is a square ring structure made of graphite material to reduce friction with the base.
8. A measuring method is suitable for measuring the seal stiffness rate and the hysteresis rate of a measured piece, and is characterized by comprising the following steps:
s801, arranging a sealing runway in a sealing area, wherein the sealing runway is sleeved by the tested piece, and the outer surface of the tested piece abuts against the sealing area; a friction piece made of flexible materials is filled in a circumferential part area of the sealing track; an opening or a gap is formed in a preset position of the sealing track, and a detected piece and/or the sealing track divide the sealing area into a high-pressure side and a low-pressure side when high-pressure gas is supplemented;
s802, when the sealing runway is not sleeved by the tested piece, acquiring a first force F of the sealing runway pushed by a thrust device to be appointed or preset to be displacedycAnd, a second force F that moves the predetermined bit back to the initial positionhc；
S803, when the closed area is in a zero-pressure environment and the sealing runway is sleeved by the tested piece, acquiring a third force F of the sealing runway pushed by a thrust device to be appointed or preset to be displacedy0And, a fourth force F that moves the predetermined position back to the initial positionh0；
S804, under the preset high-pressure environment, when the pressure difference between the high-pressure side and the low-pressure side is a preset value, acquiring a fifth force F of the sealing runway pushed by a thrust device to be appointed or preset to displaceyiAnd, a sixth force F that moves the predetermined position back to the initial positionhi；
And S805, determining the seal rigidization rate and the hysteresis rate of the tested piece according to the force of the thrust device in different environments.
9. The method of claim 8, wherein determining the seal stiffness and hysteresis rates of the test piece comprises:
determining the pressure stroke rigidity K of the tested sealing device according to the force of the thrust device under different environmentsyiReturn stiffness KhiAnd satisfies the following conditions:
Kyi＝(Fyi-Fyc)/D
Khi＝(Fhi-Fhc) D, wherein D is a preset displacement;
retardation rate sigmaiAnd a rate of rigidification δiRespectively satisfy:
σi＝(Kyi-Khi)/Kyi，δi＝Kyi/Kyo。
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| CN202111223581.1A CN114166478B (en) | 2021-10-20 | 2021-10-20 | Method and device for measuring hysteresis rate of seal rigidization rate |
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| CN202111223581.1A CN114166478B (en) | 2021-10-20 | 2021-10-20 | Method and device for measuring hysteresis rate of seal rigidization rate |
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| CN114166478B CN114166478B (en) | 2023-09-05 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6196550B1 (en) * | 1999-02-11 | 2001-03-06 | Alliedsignal Inc. | Pressure balanced finger seal |
| US6364316B1 (en) * | 1999-02-11 | 2002-04-02 | Honeywell International Inc. | Dual pressure balanced noncontacting finger seal |
| CN101749055A (en) * | 2009-12-25 | 2010-06-23 | 中国燃气涡轮研究院 | Involute-type fingertip sealing structure |
| CN106567747A (en) * | 2016-10-08 | 2017-04-19 | 清华大学 | Low-hysteresis contact type fingertip seal with fin |
| CN107702868A (en) * | 2017-08-15 | 2018-02-16 | 沈阳航空航天大学 | A kind of brush seal experimental apparatus for capability vdiverse in function |
| CN108005793A (en) * | 2017-12-27 | 2018-05-08 | 中国航发四川燃气涡轮研究院 | A kind of tile sealing structure |
| CN110195617A (en) * | 2019-07-19 | 2019-09-03 | 中国航发沈阳发动机研究所 | A kind of finger sealing device |
| CN113028059A (en) * | 2021-04-15 | 2021-06-25 | 中国航发湖南动力机械研究所 | Bearing cavity dynamic seal device and aircraft engine thereof |
-
2021
- 2021-10-20 CN CN202111223581.1A patent/CN114166478B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6196550B1 (en) * | 1999-02-11 | 2001-03-06 | Alliedsignal Inc. | Pressure balanced finger seal |
| US6364316B1 (en) * | 1999-02-11 | 2002-04-02 | Honeywell International Inc. | Dual pressure balanced noncontacting finger seal |
| CN101749055A (en) * | 2009-12-25 | 2010-06-23 | 中国燃气涡轮研究院 | Involute-type fingertip sealing structure |
| CN106567747A (en) * | 2016-10-08 | 2017-04-19 | 清华大学 | Low-hysteresis contact type fingertip seal with fin |
| CN107702868A (en) * | 2017-08-15 | 2018-02-16 | 沈阳航空航天大学 | A kind of brush seal experimental apparatus for capability vdiverse in function |
| CN108005793A (en) * | 2017-12-27 | 2018-05-08 | 中国航发四川燃气涡轮研究院 | A kind of tile sealing structure |
| CN110195617A (en) * | 2019-07-19 | 2019-09-03 | 中国航发沈阳发动机研究所 | A kind of finger sealing device |
| CN113028059A (en) * | 2021-04-15 | 2021-06-25 | 中国航发湖南动力机械研究所 | Bearing cavity dynamic seal device and aircraft engine thereof |
Non-Patent Citations (6)
| Title |
|---|
| 王栋;陈国定;安晓宁;: "指尖密封迟滞特性的当量优化研究" * |
| 王栋;陈国定;安晓宁;: "指尖密封迟滞特性的当量优化研究", 机械设计与制造, vol. 2012, no. 09, pages 48 - 52 * |
| 白花蕾: "圆弧型线指尖密封结构的形成方法和迟滞性能分析", vol. 40, no. 3 * |
| 苏华: "指尖密封结构和性能的设计分析与试验研究", pages 23 * |
| 苏华;陈国定;: "指尖密封迟滞特性的机理分析" * |
| 苏华;陈国定;: "指尖密封迟滞特性的机理分析", 机械工程学报, no. 05 * |
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