CN109520741A - A kind of aeroengine combustor buring room casing pressure experimental device - Google Patents
A kind of aeroengine combustor buring room casing pressure experimental device Download PDFInfo
- Publication number
- CN109520741A CN109520741A CN201811269035.XA CN201811269035A CN109520741A CN 109520741 A CN109520741 A CN 109520741A CN 201811269035 A CN201811269035 A CN 201811269035A CN 109520741 A CN109520741 A CN 109520741A
- Authority
- CN
- China
- Prior art keywords
- axial
- chamber
- ante
- annulus
- plate
- Prior art date
Links
- 238000002485 combustion reactions Methods 0.000 claims abstract description 47
- 238000007789 sealing Methods 0.000 claims abstract description 47
- 238000000280 densification Methods 0.000 claims description 28
- 238000004088 simulation Methods 0.000 claims description 18
- 239000007789 gases Substances 0.000 claims description 12
- 230000004301 light adaptation Effects 0.000 claims description 3
- 239000000463 materials Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 4
- 239000010720 hydraulic oils Substances 0.000 abstract description 3
- 230000001360 synchronised Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 5
- 238000000034 methods Methods 0.000 description 3
- 239000000203 mixtures Substances 0.000 description 3
- 238000010586 diagrams Methods 0.000 description 2
- 238000004364 calculation methods Methods 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 239000010948 rhodium Substances 0.000 description 1
- 239000000565 sealants Substances 0.000 description 1
- 230000003068 static Effects 0.000 description 1
- 238000006467 substitution reactions Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
Description
Technical field
The application belongs to Aeroengine Combustor Test technical field, in particular to a kind of aeroengine combustor buring room machine Casket pressure experimental device.
Background technique
Combustion box bears high temperature and pressure and big airload in use, is mainly holding for aero-engine One of power part, failure mode may be volatile, and the influence of risk is caused to aircraft, lead to catastrophic destruction, Therefore the verifying of intensity and service life must be carried out to combustion box, to guarantee Flight Safety, that in Fig. 1 is a kind of typical case Aeroengine combustor buring room casing sectional view, wherein will be set as the section A, B-section and the section C in three sections, and be applied to combustion The load burnt on the casing of room is divided into differential pressure loading and two kinds of axial force load, only forms a sealing inner cavity in the prior art, Different differential pressure loadings can not be applied in combustion box component different parts in the same time, and not account for axial force and ask Topic.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of aeroengine combustor buring room casing pressure experimental devices for the purpose of the application, to solve or overcome Problem at least one of existing in the prior art.
The technical solution of the application is:
A kind of aeroengine combustor buring room casing pressure experimental device, comprising:
Discoid bottom plate offers first through hole along axle center,
Tubular ante-chamber densification device, axial one end end and the concentric sealed connection of the bottom plate, the ante-chamber envelope The axial other end end of tight device and the ante-chamber of the combustion box are tightly connected；
Front simulation casing annular in shape is coaxially set in outside the ante-chamber densification device, the axis of the front simulation casing It is connect to one end end with the bottom plate co-axial seal, axial other end end part seal is connected to the combustion box ante-chamber End；
The ante-chamber inlet nozzle and ante-chamber exhaust apparatus opened up on the combustion box outer wall；
Support tube, axial one end are coaxially set in inside the ante-chamber densification device, and the axial other end is sealedly connected with Panel, the top panel are equipped with the first annulus and the second annulus towards the end face of the combustion box, first annulus Diameter is greater than the diameter of second annulus, axial direction on the top panel between first annulus and second annulus The second through-hole is offered, is axially arranged with third through-hole on plate the upper surface of between second annulus and the support tube；
B-section loaded ring, co-axial seal are sheathed between first annulus and second annulus, and with the burning The B-section of room casing is tightly connected；
The section C loaded ring, co-axial seal are set on the first annulus outer wall, and are cut with the C of the combustion box Face is tightly connected；
Tubular load-bearing frame, axial one end are closed end, and the other end is open end, and the closed end offers the 4th Through-hole, the open end are tightly connected towards the top panel and with the top panel；
Casing is simulated after tubular, axial one end is connect with the back cavity end part seal of the combustion box；
The section A loaded ring, co-axial seal are set on the outer wall of the load-bearing frame, and the axis with the rear simulation casing It is tightly connected to the other end；
Back cavity gas deflation assembly and back cavity inlet nozzle, on the rear cavity outer wall that the combustion box is set；Wherein, institute It states ante-chamber exhaust apparatus and back cavity gas deflation assembly is respectively communicated with the closing inner chamber of position, and be located at the top of place closing inner chamber End；
King-bolt coaxially passes through the first through hole, the ante-chamber densification device, the support tube and the four-way The axial ends adaptation in hole, the king-bolt is equipped with big nut.
Optionally, the first pressure is respectively equipped on the inside of axial one end of the bottom plate and the bottom surface of the ante-chamber densification device Plate and the second pressing plate, and the bottom plate is connect with the ante-chamber densification device by compression by the king-bolt and big nut.
Optionally, the first bolt assembly between the bottom plate and the ante-chamber densification device by being circumferentially evenly arranged Connection.
Optionally, sealing ring is equipped between the bottom plate and the ante-chamber densification device.
Optionally, using interference fit between the B-section loaded ring and first annulus and second annulus, and It is provided with sealing ring.
Optionally, connected between the B-section loaded ring and the B-section of the combustion box using the second bolt assembly It connects, and is provided with sealing ring.
Optionally, the sealing ring is made of rubber material.
Optionally, the third through-hole connects pump nozzle.
Optionally, floor is installed in the load-bearing frame.
Optionally, it is connected between the front simulation casing and the bottom plate using screw.
At least there are following advantageous effects in the application:
The aeroengine combustor buring room casing pressure experimental device of the application, solves the same time in aero-engine Combustion box different parts apply the difficult point of different differential pressure loadings, realize and accurately apply the function of axial force in installation side section And differential pressure loading load synchronous with axial force load.
Detailed description of the invention
Fig. 1 is the sectional view of the combustion box of the application；
Fig. 2 is the sectional view of the combustion box pressure experimental device of the application；
Fig. 3 is the combustion box load schematic of the application；
Fig. 4 is the section C Axial Force Calculating schematic diagram in embodiments herein；
Fig. 5 is exhaust apparatus schematic diagram in embodiments herein；
Wherein:
The section 1-A loaded ring simulates casing, 3- combustion box, 4- load-bearing frame, 5- back cavity gas deflation assembly, 6-C after 2- Section loaded ring, the section 7-B loaded ring, 8- ante-chamber exhaust apparatus, 9- front simulation casing, 10- bottom plate, the first pressing plate of 11-, 12- Support tube, 13- big nut, 14- king-bolt, the second pressing plate of 15-, 16- ante-chamber densification device, 17- ante-chamber inlet nozzle, 18- back cavity Inlet nozzle.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear", The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application The limitation of range.
1 to Fig. 5 the application is described in further details with reference to the accompanying drawing.
As shown in Fig. 2, the space shuttle combustion box pressure experimental device of the application, comprising:
Discoid bottom plate 10, offers first through hole along axle center,
Tubular ante-chamber densification device 16, axial one end end and the concentric sealed connection of bottom plate 10, ante-chamber obturage dress It sets 16 axial other end end and the ante-chamber of combustion box 3 is tightly connected；
Front simulation casing 9 annular in shape, is coaxially set in outside ante-chamber densification device 16, and axial the one of front simulation casing 9 End end is connect with 10 co-axial seal of bottom plate, and axial other end end part seal is connected to the end of 3 ante-chamber of combustion box；
The ante-chamber inlet nozzle 17 and ante-chamber exhaust apparatus 8 opened up on 3 outer wall of combustion box；
Support tube 12, axial one end are coaxially set in inside ante-chamber densification device 16, and the axial other end is sealedly connected with Panel, top panel are equipped with the first annulus and the second annulus towards the end face of combustion box 3, and the diameter of the first annulus is greater than second The diameter of annulus axially offers the second through-hole, the second annulus and branch the upper surface of between the first annulus and the second annulus on plate Third through-hole is axially arranged on plate the upper surface of between stay tube 12；
B-section loaded ring 7, co-axial seal are sheathed between the first annulus and the second annulus, and the B with combustion box 3 Cross section sealing connection；
The section C loaded ring 6, co-axial seal are set on the first annulus outer wall, and the C cross section sealing with combustion box 3 Connection；
Tubular load-bearing frame 4, axial one end are closed end, and the other end is open end, and closed end offers four-way Hole, open end are tightly connected towards top panel and with top panel；
Casing 2 is simulated after tubular, axial one end is connect with the back cavity end part seal of combustion box 3；
The section A loaded ring 1, co-axial seal is set on the outer wall of load-bearing frame 4, and axial another with rear simulation casing 2 One end is tightly connected；
Back cavity gas deflation assembly 5 and back cavity inlet nozzle 18, on the rear cavity outer wall that combustion box 3 is set；Wherein, preceding Chamber exhaust apparatus 8 and back cavity gas deflation assembly 5 are respectively communicated with the closing inner chamber of position, and are located at the top of place closing inner chamber End；
King-bolt 14 coaxially passes through first through hole, ante-chamber densification device 16, support tube 12 and fourth hole, king-bolt 14 axial ends adaptation is equipped with big nut 13.
In the present embodiment, bottom plate 10, front simulation casing 9, combustion box ante-chamber, the section C loaded ring 6, the first annulus, P1 sealing inner cavity is confined between B-section loaded ring 7 and ante-chamber densification device 16；Ante-chamber densification device 16, support tube 12, Top panel, the second annulus, B-section loaded ring 7 and and combustion box before P2 sealing inner cavity is confined between cavity inner sleeve；The section C Loaded ring 6, the first annulus, combustion box back cavity, rear simulation casing 2, the section A loaded ring 1, load-bearing frame and top panel Between be confined to P3 sealing inner cavity；
P1 sealing inner cavity has been respectively communicated with ante-chamber inlet nozzle 17 and ante-chamber exhaust apparatus 8, and ante-chamber inlet nozzle 17 is sealed to P1 Interior intracavitary oiling applies pressure, and ante-chamber exhaust apparatus 8 discharges gas intracavitary in P1 sealing, closes after emptying；P2 sealing Inner cavity has been respectively communicated with back cavity inlet nozzle 18 and back cavity inlet nozzle 5, seals inner cavity oiling pressure and exhaust for P2；In P3 sealing Chamber is connected to third through-hole, and third through-hole can connect pump nozzle and exhaust apparatus, realizes the pressurization to P3 sealing inner cavity.
In the present embodiment, first is respectively equipped on the inside of axial one end of bottom plate 10 and the bottom surface of ante-chamber densification device 16 Pressing plate 11 and the second pressing plate 15, and bottom plate 10 is connect pressure with ante-chamber densification device 16 with big nut 14 by the king-bolt 13 passed through Tightly, king-bolt 13 and big nut 14 add the first pressing plate 11 and the second pressing plate as main load component in the application device 15 ensure that the stable safety of device in test.
Meanwhile it being connected between bottom plate 10 and ante-chamber densification device 16 by the first bolt assembly being circumferentially evenly arranged.
In the present embodiment, sealing ring is equipped between bottom plate 10 and ante-chamber densification device 16；B-section loaded ring 7 and first Using interference fit between annulus and the second annulus, and it is provided with sealing ring；The B of the section B loaded ring 7 and combustion box 3 is cut It is connected between face using the second bolt assembly, and is provided with sealing ring；Front simulation casing 9 is connected on bottom plate 10 using screw； The above are the portion connections and its connection type in the application device, it is to be appreciated that: the junction of the application device is equal Encapsulation process is carried out, what the sealing ring in the application device used is made of rubber material, in order to preferably be sealed.
In the present embodiment, floor is installed in load-bearing frame 4, increases the intensity of load-bearing frame 4, so that load-bearing frame 4 is more stable.
As shown in Fig. 2, the aeroengine combustor buring room casing pressure experimental device of the application, to the pressure to casing Detection and the detection of axial force carry out the installation such as Fig. 2, wherein to combustion box pressure to this experimental rig first Detection method is: by sealing inner cavity to P1, P2 seals inner cavity and P3 seals inner cavity and pressurizes, and the size of pressure value passes through Pressure sensor feedback, when pressurization, may know that the size of pressure value, casing housing leading portion differential pressure loading △ P1=P1, after housing Differential pressure loading △ P2=P2 is held, in order to detect the pressure of inner sleeve receiving, pressurizes to P3 sealing inner cavity, applies pressure P3, this When casing inner sleeve inside and outside two surfaces have different pressure, actual differential pressure loading △ P3=P1-P2, to three when test Sealing inner cavity is pressurizeed simultaneously, can be detected the pressure value of three sealing inner cavities.
The axial force of combustion box is that casing internal pressure load is acted on the loaded ring of interface and realized, therefore, Detection to casing pressure loading is also the detection to a interface axial force load, as shown in figure 3, axial force F A is by pressure loading P2 acts on the section A loaded ring 1 in Fig. 2 and applies, and axial force F B acts on B in Fig. 2 by pressure loading P1 and pressure loading P3 and cuts Face loaded ring 7 applies, and axial force F C acts on the section C loaded ring 6 in Fig. 2 by pressure loading P1 and pressure loading P2 and applies, real The function of axial force load is showed.
In the present embodiment, by taking the section C as an example, loading method is: accurately to apply axial force load at the section C, considering Influence of the apparatus system error to axial force load caused by the frictional force of sealing ring, tooling deform etc. under load effect；
The section (such as Fig. 4) C axial force:
Fc=Fp+Fw (1)
In formula,
Fc --- the section C axial force, N；
The axial force that Fp --- differential pressure loading generates, N；
Fw --- the systematic error in the axial force of the section C；
The axial force F p calculation method that P1 pressure loading and P2 pressure loading collective effect generate on the loaded ring of the section C is such as Under:
In formula,
Fp --- the section C axial force, N；
P1 --- P1 seals inner cavity internal pressure, MPa；
P2 --- P2 seals inner cavity internal pressure, MPa；
D1 --- side outer diameter, mm are installed in the intracavitary section C in P2 sealing；
D2 --- side internal diameter, mm are installed in the intracavitary section C in P1 sealing；
D3 --- switching tooling outer diameter, mm；
The error of experimental rig is divided into systematic error and two kinds of random error, and systematic error can be corrected, and random error is not It can correct.In order to reduce influence of the systematic error to axial force load, in experimental rig design process, analysis, which considers, is The composition for error of uniting.Systematic error mainly includes two kinds: combustion box deforms under pressure causes the section C loaded ring to hold Caused by the frictional force that sealing ring generates at axial force variation caused by pressure area of section changes and the section C loaded ring Axial force variation.
Fw=Ff+ △ Fd (3)
In formula,
Ff --- frictional force at the section C, N；
Differential pressure loading changing value, N caused by △ Fd --- casing deforms；
Frictional force two parts caused by the frictional force of sealing ring frictional force caused by precommpression and hydraulic fluid pressure form, Two be added sealing ring generate total frictional force:
In formula,
F --- the coefficient of friction between sealing ring and contact surface；
D --- seal diameter, mm；
W --- sealing ring diameter of section, mm；
μ --- sealing ring Poisson's ratio；
E --- sealing ring elasticity modulus, MPa；
E --- Compress rate of sealing ring；
P --- sealing ring operating pressure, MPa.
In formula,
P1 --- P1 seals inner cavity internal pressure, MPa；
P2 --- P2 seals inner cavity internal pressure, MPa；
d1' --- side outer diameter, mm are installed in the intracavitary section C in P2 sealing after deformation；
d'2--- side internal diameter, mm are installed in the intracavitary section C in P1 sealing after deformation；
d3' --- switching tooling outer diameter after deformation, mm；
A variety of seal means, which are applied in combination, in device in the present embodiment makes experimental rig integrally achieve preferable sealing effect Fruit.By deformation of the finite element analysis experimental rig in maximum test load, the biggish structure of radial deformation is used Axial seal uses radial seal to the biggish structure of axial deformation, and avoiding the loaded deformation of structure leads to the wind of seal failure Danger.It is smaller to some deformations, while the structure that sealing space is limited, it is sealed using flat sealant.Three kinds of seal means combinations Using having reached preferable sealing effect.
In the present embodiment, realize that pressurizing load, the hydraulic load of pressurization have load peace using filling hydraulic oil Entirely, the fast feature of pressurization release, compared with the safe and easy control of gas pressure loads, in the device of the application when filling hydraulic oil, It needs that gas is discharged, the exhaust that the ante-chamber exhaust apparatus 8 and back cavity gas deflation assembly 5 being illustrated in figure 5 in the application device are applied Device has one section of longer exhaust pipe in the device, is placed on the top of closing inner chamber, with the gas for facilitating discharge more as far as possible.
Unit simulation in the application boundary condition of test, wherein rear simulation casing 2 and front simulation casing 9 and combustion The rear and front end for burning room casing housing is connected, and the size under analog machine is designed by formula (6), is simulated and combustion chamber machine The rigidity for the casing that casket is connected avoids test boundary condition and the inconsistent influence to test result of actual boundary condition.
L>5(Rh)0.5 (6)
In formula,
The length of L- simulation casing；
R- switching casing mean radius；
H- switching casing wall thickness.
The device of the application can also realize the static strength of combustion box and the examination of fatigue strength.
The aeroengine combustor buring room casing pressure experimental device of the application, solves the same time in aero-engine Combustion box different parts apply the difficult point of different differential pressure loadings, realize and accurately apply the function of axial force in installation side section And differential pressure loading load synchronous with axial force load.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims It is quasi-.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811269035.XA CN109520741A (en) | 2018-10-29 | 2018-10-29 | A kind of aeroengine combustor buring room casing pressure experimental device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811269035.XA CN109520741A (en) | 2018-10-29 | 2018-10-29 | A kind of aeroengine combustor buring room casing pressure experimental device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109520741A true CN109520741A (en) | 2019-03-26 |
Family
ID=65772623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811269035.XA CN109520741A (en) | 2018-10-29 | 2018-10-29 | A kind of aeroengine combustor buring room casing pressure experimental device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109520741A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595668A (en) * | 2019-09-17 | 2019-12-20 | 中国航发沈阳发动机研究所 | Engine performance test piece machine casket inner chamber measurement structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2995996A1 (en) * | 2012-09-26 | 2014-03-28 | Snecma | Measurement device for measuring parameters of combustion chamber of gas turbine engine mounted on test bench, has elbow connecting rectilinear portions of tube, where elbow presents oblong section |
| CN104236804A (en) * | 2014-09-22 | 2014-12-24 | 西安航空动力股份有限公司 | Pressure test tool with function of axial deformation compensation |
| CN105319047A (en) * | 2015-10-20 | 2016-02-10 | 四川成发航空科技股份有限公司 | Aero-engine casing through-flow pore flow testing method and implementation device thereof |
| CN105445026A (en) * | 2015-11-23 | 2016-03-30 | 成都发动机（集团）有限公司 | Device used for hydraulic test of aero-engine combustion chamber case diffuser |
| CN205941217U (en) * | 2016-08-04 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Compression test varying axial is to power loading device |
-
2018
- 2018-10-29 CN CN201811269035.XA patent/CN109520741A/en active Search and Examination
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2995996A1 (en) * | 2012-09-26 | 2014-03-28 | Snecma | Measurement device for measuring parameters of combustion chamber of gas turbine engine mounted on test bench, has elbow connecting rectilinear portions of tube, where elbow presents oblong section |
| CN104236804A (en) * | 2014-09-22 | 2014-12-24 | 西安航空动力股份有限公司 | Pressure test tool with function of axial deformation compensation |
| CN105319047A (en) * | 2015-10-20 | 2016-02-10 | 四川成发航空科技股份有限公司 | Aero-engine casing through-flow pore flow testing method and implementation device thereof |
| CN105445026A (en) * | 2015-11-23 | 2016-03-30 | 成都发动机（集团）有限公司 | Device used for hydraulic test of aero-engine combustion chamber case diffuser |
| CN205941217U (en) * | 2016-08-04 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Compression test varying axial is to power loading device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595668A (en) * | 2019-09-17 | 2019-12-20 | 中国航发沈阳发动机研究所 | Engine performance test piece machine casket inner chamber measurement structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101625026B (en) | Resilient high pressure metal-to-metal seal and method | |
| EP2002080B1 (en) | Sealing device | |
| US7827853B2 (en) | Weld testing apparatus and method for nozzles | |
| RU2454558C2 (en) | Dynamic brush seal, turbine with said seal and gas turbine engine | |
| US6823719B2 (en) | Method and apparatus to locally test pressure seal | |
| JP5439269B2 (en) | Filling passage opening and closing device for liquid filling machine | |
| US7523644B2 (en) | Method and apparatus for verifying the integrity of a joint seal | |
| KR101952476B1 (en) | Control valve monitoring system | |
| US9989157B2 (en) | Valve vented redundant stem seal system | |
| US9206670B2 (en) | Independent dual actuated subsurface safety valve | |
| EP2860102B1 (en) | Shrink strut landing gear system | |
| JP5378526B2 (en) | Gate valve | |
| CN101218456B (en) | Slide ring seal | |
| US20040101395A1 (en) | System to control axial thrust loads for steam turbines | |
| US2691773A (en) | Valve leak detector | |
| EP2547996B1 (en) | Retrievable pressure sensor | |
| US20030133792A1 (en) | Composite tubular woven seal for an inner compressor discharge case | |
| US9541151B2 (en) | Dual stage shock strut with removable second stage fluid chamber | |
| CN101589236B (en) | Multi-stage high-pressure pump | |
| US4373862A (en) | Rotor blade shaft integrity monitoring system | |
| US8104291B2 (en) | Combustion cap floating collar using E-seal | |
| RU2551453C2 (en) | Multistage rotor with coupling bolt and flange secured by bolts and method of assembly | |
| EP2957798A1 (en) | High temperature valve | |
| CN202362120U (en) | Device for quickly detecting air tightness | |
| US7954550B2 (en) | Tubing pressure insensitive control system |
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 |