CN105319069B - A kind of device and its stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure - Google Patents
A kind of device and its stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure Download PDFInfo
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- CN105319069B CN105319069B CN201510788086.3A CN201510788086A CN105319069B CN 105319069 B CN105319069 B CN 105319069B CN 201510788086 A CN201510788086 A CN 201510788086A CN 105319069 B CN105319069 B CN 105319069B
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Abstract
The present invention relates to a kind of devices and its stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure, the stagnation pressure tube is the structure of segmented, pressure-measuring pipe nozzle is removably sealedly connected on the rear end of cannula part by connector, cannula part is the straight-bar and its outer diameter extended along the longitudinal direction less than the aperture for being intubated mounting hole, therefore the air inlet of stagnation pressure tube is when depositing a large amount of metallics and afterburning room housing cannot be withdrawn from from rear, need to only the connection structure of other on cannula part be removed can be fully inserted into cannula part in afterburning room housing and take out it from engine jet pipe exit, the metallic nearby deposited to cannula part air inlet again after taking-up is cleared up.Avoiding problems being stretched into instrument in afterburning chamber by jet pipe to cause a series of problems to deposited particles cleaning at air inlet, the dismounting rate of stagnation pressure tube is effectively improved, improves the service life of the device and the service life of engine product.
Description
Technical field
The present invention relates to the one kind used in the direct-connect test technology of Ducted rocket ground to be used for Ducted rocket afterburning
The device and its stagnation pressure tube of room stagnation pressure test.
Background technology
In the development process of Ducted rocket, ground experiment is an important ring, only passes through ground experiment, Cai Nengfa
The key technical problem occurred in now being developed with solution, finally develops the engine for meeting technical indicator.Direct-connect test is
A kind of most simple and most economical test method, by simulating the stagnation pressure and total temperature of incoming, reaches mould in punching engine experiment
Send out the purpose of motivation internal flow.Engine is mainly made of air intake duct, gas generator, afterburning chamber and punching press jet pipe,
Fuel rich propellant is loaded in middle gas generator, boosting powder column is filled in afterburning chamber, when the boosting powder column burning in stamping combustion chamber
After complete, engine flight reaches relay point and turns grade Mach number, and then boosting jet pipe is disposed, and air intake duct blanking cover is opened, with
Gas generator is started to work simultaneously for this, and the fuel-rich combustion gas generated by fuel rich propellant enters ramjet combustor, and by air intake duct
The air of entrance is blended and second-time burning occurs, and is finally discharged via jet pipe, generates thrust.And it is sent out in solid-rocket punching press
In the course of work of motivation, it is shadow that can the air of fuel-rich combustion gas and air intake duct introducing carry out HIGH-EFFICIENCY POST-COMBUSTION in afterburning chamber
One of key technology of punching engine performance is rung, so needing to measure the air-flow stagnation pressure of afterburning chamber.
Home and abroad measures air-flow stagnation pressure using pitot-type stagnation pressure tube at present, principle as shown in Figure 1, be in face of
Direction of flow arranges a probe, and by incoming semistall, the pressure for measuring stagnant air is stagnation pressure.Concrete structure such as Fig. 2
It is shown, including being installed in the pressure measurement seat 2 in afterburning room housing 1 and being in outside afterburning chamber, afterburning is stretched by the through hole on pressure measurement seat 2
The middle part of cannula part 12 inside room housing 1 is provided with the air intake duct that both ends penetrate through cannula part 12 along its length, into
The front opening of air flue is the air inlet towards direction of flow, is provided in the middle part of pressure-measuring pipe nozzle and is connected with the rear end of the air intake duct
Venthole.The structure of stagnation pressure tube as shown in figure 3, including rear end for connecting the pressure-measuring pipe nozzle of pressure sensor and front end
Cannula part 12, it is larger so that foring step on cannula part 12 to connect the outer diameter of the pressure sensor pressure-measuring pipe nozzle of rear end
Face, in order to ensure the accuracy of pressure measurement, the through hole stretched into for cannula part 12 in afterburning room housing 1 and pressure measurement seat 2
The outer diameter of aperture and cannula part, which matches and is slightly larger than the outer diameter of cannula part, can swimmingly be inserted into afterburning room housing 1
It is interior.Cannula part is fixed on by sealing fixed seat on pressure measurement seat 2, and sealing fixed seat includes being sleeved on cannula part outer circumferential surface
Copper washer 5, mounted on the mounting base 4 of the front and rear sides of copper washer 5 and clamp nut 6, cannula part is pressed from both sides by copper washer 5
Tightly, 4 Screw assembly of mounting base is equipped with gasket 3 on pressure measurement seat 2 between mounting base 4 and pressure measurement seat 2.Before cannula part 12
When end is stretched into afterburning room housing 1 to measure Ducted rocket afterburning chamber stagnation pressure, cannula part 12 is in face of fuel gas flow direction one
Side has a large amount of metal particle depositions, it is difficult to cannula part is withdrawn from into pressure measurement seat 2 by rear, while pressure-measuring pipe nozzle is in cannula part
The step surface that 12 rear end is formed cause pressure-measuring pipe nozzle can not pass through pressure measurement seat and afterburning room housing and from the engine in front
Stagnation pressure tube is taken out in jet pipe, instrument can only be cleaned up what stagnation pressure tube air inlet nearby deposited by being stretched into jet pipe in afterburning chamber
Stagnation pressure tube could be withdrawn from afterburning room housing by rear after metallic.This not only causes the cleaning of stagnation pressure tube, dismounting difficulty,
The damage of stagnation pressure tube and jet pipe is also easily caused during clearing up stagnation pressure tube.
The content of the invention
It is an object of the invention to provide a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure is existing to solve
Test device is caused by due to the deposition of condensed-phase particle the problem of stagnation pressure tube dismounting difficulty；On providing
State the stagnation pressure tube used in test device.
To solve the technical problem, a kind of device stagnation pressure for the test of Ducted rocket afterburning chamber stagnation pressure of the invention
Pipe uses following technical scheme：
A kind of device stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure passes through afterburning room housing including front end
And after the intubation mounting hole that correspondence penetrates through on pressure measurement seat stretches into the cannula part of afterburning chamber enclosure interior and is connected in cannula part
The pressure-measuring pipe nozzle at end, the outer diameter of the pressure-measuring pipe nozzle are more than the diameter of intubation mounting hole；It is provided in the middle part of cannula part along its length
The extension of degree direction, both ends penetrate through the air intake duct of the cannula part, and the entrance of the front end of air intake duct is towards direction of flow, pressure measurement
The venthole being connected with the rear end of the air intake duct is provided in the middle part of pipe nozzle；The cannula part is split knot with pressure-measuring pipe nozzle
Structure, cannula part is the straight-bar that axis extends along the longitudinal direction and its outer diameter is less than the aperture of the intubation mounting hole so that it can
Afterburning chamber enclosure interior is fully inserted into, after the pressure-measuring pipe nozzle is removably sealedly connected on cannula part by connector
End.
Venthole on the pressure-measuring pipe nozzle is the pre-large post-small stepped hole of diameter, and the macropore of front end is included for cannula part
The outer diameter closely inserted, the diameter of the aperture of rear end are identical with the aperture of air intake duct.
A kind of device for the test of Ducted rocket afterburning chamber stagnation pressure of the present invention uses following technical scheme：
A kind of device for the test of Ducted rocket afterburning chamber stagnation pressure is fixed on including stagnation pressure tube and by the stagnation pressure seal of tube
Pressure measurement seat in afterburning room housing, stagnation pressure tube include front end and are installed by the intubation of corresponding perforation in afterburning room housing and pressure measurement seat
Hole stretches into the cannula part of afterburning chamber enclosure interior and is connected in the pressure-measuring pipe nozzle of cannula part rear end, outside the pressure-measuring pipe nozzle
Footpath is more than the diameter of intubation mounting hole；Extension, both ends along its length are provided in the middle part of cannula part and penetrate through the intubation
Partial air intake duct, the entrance of the front end of air intake duct are provided with and the air intake duct in the middle part of pressure-measuring pipe nozzle towards direction of flow
The venthole that rear end is connected；The cannula part is Split type structure with pressure-measuring pipe nozzle, and cannula part prolongs along the longitudinal direction for axis
The straight-bar stretched and its outer diameter are less than the aperture of the intubation mounting hole so that it can be fully inserted into afterburning chamber enclosure interior, the survey
Pressure pipe nozzle is removably sealedly connected on the rear end of cannula part by connector.
The connector includes the clamp part being set in by the installation through-hole at middle part on cannula part, fixes clamp part
Locking member on cannula part and pressure-measuring pipe nozzle is fixed on the pressure cap on clamp part；The clamp part for before rear big it is small not
Isometrical body, the forepart of clamp part are fixed on the corresponding position of cannula part, the rear end of clamp part by the locking member
Middle part open up it is fluted, the pressure-measuring pipe nozzle be partially submerged into be mounted on the groove in, the pressure cap is connected through a screw thread closely
Ground is set in the rear end of clamp part and the rear end of cannula part will be closely pressed in pressure-measuring pipe nozzle between the two.
Venthole on the pressure-measuring pipe nozzle is the pre-large post-small stepped hole of diameter, and the macropore of front end is included for cannula part
The outer diameter closely inserted, the diameter of the aperture of rear end are identical with the aperture of air intake duct.
The clamp part includes the cone section with interior receipts inclined surface of forepart, circumferentially spaced in the cone section to offer at least
Two along pressure pipe part length direction extend gap, the gap in the axial direction front opening back-end closure, pass through on the radial
The wall thickness of the clamp part is worn, which, which to bore in section, forms the fingertip that can radially elasticly actuate；The locking member is
The locking nut being set in the cone section, the forepart of locking nut are equipped with the inclined surface identical with the gradient of the cone section, to
After when screwing locking nut fingertip clamp cannula part to contract, so as to fulfill the fixation to cannula part.
Airtight and watertight padding is filled between the pressure-measuring pipe nozzle and cannula part to ensure between cannula part and clamp part
Sealing effect.
The copper washer that the semicircle gasket that the sealing fixed seat includes mainly being mutually matched by two panels forms.
Pressure-measuring pipe nozzle of the prior art is integrally formed to constitute the stagnation pressure with step surface at the rear portion of cannula part
Pipe, so when the air inlet of stagnation pressure tube deposits a large amount of metallics and when cannot withdraw from afterburning room housing from rear, afterburning chamber shell
The through hole identical with cannula part outer diameter opened up on body and on pressure measurement seat also counteracts engine jet pipe of the stagnation pressure tube from front
In withdraw from afterburning room housing, can only by instrument by stretched into jet pipe in afterburning chamber clean up stagnation pressure tube air inlet nearby deposit gold
Stagnation pressure tube could be withdrawn from afterburning room housing by rear after belonging to particle.This not only causes the cleaning of stagnation pressure tube, dismounting difficulty,
The damage of stagnation pressure tube and jet pipe is also easily caused during clearing up stagnation pressure tube.
And a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure of the present invention is by pressure-measuring pipe nozzle and cannula part
It has made the structure of segmented and the axis of cannula part extends along the longitudinal direction, outer diameter is less than the straight of intubation installation bore dia
Bar, pressure-measuring pipe nozzle are removably sealedly connected on the rear end of cannula part by connector, so when the air inlet of stagnation pressure tube sinks
When accumulating a large amount of metallics and afterburning room housing cannot be withdrawn from from rear, the pressure-measuring pipe nozzle and connector of rear end need to only be removed,
Cannula part can be fully inserted into afterburning room housing by unscrewing clamp nut again, by cannula part from engine jet pipe exit
It takes out, the metallic nearby deposited to cannula part air inlet again after taking-up is cleared up.This is effectively improved to stagnation pressure
The rate that pipe is dismantled, while will not be to engine jet pipe and stagnation pressure tube in the cleaning work that afterburning chamber hull outside carries out
It damages, is conducive to improve the service life of the device and the service life of engine product.
Description of the drawings
Fig. 1 is stagnation pressure test philosophy schematic diagram；
Fig. 2 is the structure diagram that total compression testing device stretches into afterburning room housing in the prior art；
Fig. 3 is the structure diagram of stagnation pressure tube in the prior art；
Fig. 4 is that a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure in the present invention is stretched into afterburning room housing
Structure diagram；
Fig. 5 is the structure diagram that the cannula part in Fig. 4 is attached with pressure-measuring pipe nozzle by connector；
Fig. 6 is the structure diagram of clamp part in Fig. 5.
Specific embodiment
A kind of embodiment of device for the test of Ducted rocket afterburning chamber stagnation pressure：
A kind of structure of device for the test of Ducted rocket afterburning chamber stagnation pressure is as shown in Fig. 4 ~ 6, including afterburning chamber shell
Body 1 and the pressure measurement seat 2 being connected in outside afterburning room housing 1, in afterburning room housing 1 and pressure measurement seat 2 it is corresponding offer diameter it is identical,
The through hole being mutually communicated（It is intubated mounting hole）, outer diameter is slightly less than the diameter of above-mentioned through hole to ensure the cannula part of airtight effect
12 are inserted into the through hole, and the middle part of cannula part 12 is provided with extension, both ends along its length and penetrates through cannula part 12
Air intake duct, and its front end is stretched into inside afterburning room housing 1, air inlet is towards direction of flow, pressure-measuring pipe nozzle 7 is removable by connector
It is sealedly connected on the rear end of cannula part 12 with unloading, sealing element includes clamp part 10, clamp part 10 is fixed on cannula part 12
On locking nut 11 and the pressure cap 8 that is fixed on pressure-measuring pipe nozzle 7 on clamp part 10.
Clamp part 10 is provided with the installation to match with the outer diameter of cannula part 12 and leads to for pre-small post-large body and its middle part
Hole offers the groove 101 of the front end insertion for pressure-measuring pipe nozzle 7 on the end face of big section, and the outer surface of big section offers and pressure cap 8
The inner surface of correspondent section realize the first thread segment 102 of thread fitting, the outer diameter of segment is identical with the internal diameter of locking nut 11
And including being equipped with and locking member（It is locking nut 11 herein）The second thread segment 103 and light bar segment of thread fitting, at light bar segment
Transition position between the second thread segment 103 and the first thread segment 102 and at its both ends is machined with technology groove；The front end of segment
Cone section with interior receipts opens up that there are four prolong along the length direction of pressure pipe part in the cone section of the interior receipts along the circumferentially-spaced of segment
The gap 104 stretched, gap 104 in the axial direction front opening back-end closure, on the radial run through pressure pipe part 10 wall thickness, gap
104 in cone section so that form the fingertip 105 that can radially elasticly actuate；The front end of locking nut 11 is equipped with and pressure pipe part epicone
The identical inclined surface of gradient of section, drives fingertip 105 to clamp cannula part 12 to contract when screwing locking nut 11 backward,
So as to which pressure pipe part 10 is fixed on cannula part 12.
Pressure-measuring pipe nozzle 7 is the body of multistage step, and be followed successively by front end from front to back is mounted on groove for embedded
In the 101 and outer diameter insertion section identical with the internal diameter of groove 101, the outer diameter sealing identical with the big section outer diameter of clamp part 10
The linkage section for being used to connect sensor of section, the outer diameter cooperation section identical with the internal diameter of the correspondent section of pressure cap 8 and rearmost end.Pressure measurement
The middle part of pipe nozzle 7 is provided with the venthole for penetrating through its length, and venthole is pre-large post-small stepped hole, specifically includes the macropore of front end
And the aperture of rear end, the diameter of macropore is identical with the outer diameter of cannula part 12, diameter and the air inlet on cannula part 12 of aperture
The aperture in road is identical.
Pressure cap 8 is sleeved on the first thread segment 102 of stagnation pressure tube 10 and is pressed in pressure-measuring pipe nozzle 7 between the two, and pressure cap 8 wraps
It includes internal-and external diameter and differs pre-large post-small two sections, 102 thread fitting of the inner surface of big section and the first thread segment, the interior table of segment
Face is adapted with the cooperation section of pressure-measuring pipe nozzle 7 and the length of segment is identical with the length of the cooperation section of pressure-measuring pipe nozzle 7, so screwing
Pressure cap 8 to a certain extent when pressure-measuring pipe nozzle 7 the rear surface of seal section formed by the inner surface of its segment and the inner surface of big section
Step surface block, the front surface of seal section is axially moveable and leads to by the rear end face block of clamp part 10, then by pressure-measuring pipe nozzle 7
It crosses clamp part 10 to lock on cannula part 12, and then pressure-measuring pipe nozzle 7 can be securely pressed in the rear end face of cannula part 12
On.
The erection sequence of the device is as follows：Clamp part 10 is set on cannula part 12, adjusts its position to its rear end
Face extends slightly from the rear end face of stagnation pressure tube to ensure that the macropore that pressure-measuring pipe nozzle 7 is completely embedded into after groove 101 thereon can be partly set with
In the rear end of cannula part 12.So far locking nut 11 is sleeved on from the front to the back in the cone section of clamp part 10 behind position, revolved
Twisting locking nut 11 makes to move thereafter so that fingertip 105 is radially contracted and is pressed on cannula part 12, realizes to clamp part
10 fixation.Airtight and watertight padding 9 is packed into the gap between groove 101 and cannula part 12, then the insertion by pressure-measuring pipe nozzle 7
In the embedded groove 101 of section, cover and tighten pressure cap 8 so that clamp part 10, pressure-measuring pipe nozzle 7 and pressure cap 8 form a whole, this
When pressure-measuring pipe nozzle 7 on the forepart of macropore be closely sleeved on the rear end of cannula part 12, when screwing pressure cap 8 makes it move forward vertically
It can drive the Forward of pressure-measuring pipe nozzle 7 and the airtight and watertight padding in compressed grooves 101 and then realize clamp part 10, pressure-measuring pipe nozzle 7 with inserting
Sealing between tube portion 12 so that the air-flow entered by air admission hole is not in leakage but flows into pressure-measuring pipe nozzle 7 through air intake duct
On macropore and aperture finally flow through the sensor at 7 rear of pressure-measuring pipe nozzle to measure air pressure.By pressure-measuring pipe nozzle 7 and cannula part 12
Clamp nut 6, copper washer 5, mounting base 4 and gasket 3 are sleeved on cannula part 12 successively by front again after being fixedly connected, adjusted
Whole cannula part 12, which is stretched into afterburning room housing 1, presss from both sides two semi-circular copper washers 5 to tightening clamp nut 6 after suitable position
Tight cannula part 12 and the position of cannula part 12 is fixed on pressure measurement seat 2.
After the completion of test, unscrew pressure cap 8 and dismantle pressure-measuring pipe nozzle from cannula part 12, then unscrew locking nut 11 and incite somebody to action
Clamp part 10 and locking nut 11 are dismantled from the rear end of cannula part 12, then are unscrewed clamp nut 6 and unclamped cannula part 12
The rear end of cannula part 12 is fully inserted into afterburning room housing 1, so as to from the outlet of the engine jet pipe of afterburning chamber front end
Place takes out cannula part 12, and the metallic nearby deposited to stagnation pressure tube air inlet again after taking-up is cleared up.This is effectively
The rate dismantled to stagnation pressure tube is improved, while will not be to engine in the cleaning work that afterburning chamber hull outside carries out
Jet pipe and stagnation pressure tube damage, and are conducive to improve the service life of the device and the service life of engine product.
It in other embodiments, also can be corresponding by being set on pressure-measuring pipe nozzle and cannula part in the case of ensureing sealing
Buckle or helicitic texture realize both be detachably connected, can also by step up in the two junction cuff ring form realize
The two is detachably connected.The forepart of the clamp part is alternatively the elastic collar that can be directly set on cannula part, locking
Part can also be the structure for being mutually inserted or engaging with the corresponding construction on cannula part.It can guarantee venthole and air intake duct
In the case of concentricity, venthole can also be the diameter unthreaded hole rather than stepped hole identical with the aperture of air intake duct.
Claims (7)
1. a kind of device stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure, including front end by afterburning room housing and
The intubation mounting hole of corresponding perforation stretches into the cannula part of afterburning chamber enclosure interior and is connected in cannula part rear end on pressure measurement seat
Pressure-measuring pipe nozzle, the outer diameter of the pressure-measuring pipe nozzle is more than the diameter of intubation mounting hole；It is provided with along its length in the middle part of cannula part
Direction extension, both ends penetrate through the air intake duct of the cannula part, and the entrance of the front end of air intake duct is towards direction of flow, pressure-measuring pipe
The venthole being connected with the rear end of the air intake duct is provided in the middle part of nozzle；It is characterized in that：The cannula part and pressure-measuring pipe nozzle
For Split type structure, cannula part is the aperture that the straight-bar that axis extends along the longitudinal direction and its outer diameter are less than the intubation mounting hole
So that it can be fully inserted into afterburning chamber enclosure interior, the pressure-measuring pipe nozzle is removably sealedly connected on intubation portion by connector
The rear end divided, the connector include the clamp part being set in by the installation through-hole at middle part on cannula part, consolidate clamp part
The locking member that is scheduled on cannula part and pressure-measuring pipe nozzle is fixed on the pressure cap on clamp part；The clamp part is rear big preceding small
Waney body, the forepart of clamp part are fixed on the corresponding position of cannula part by the locking member, after clamp part
Middle part is held to open up fluted, the pressure-measuring pipe nozzle is mounted in the groove with being partially submerged into, and the pressure cap is connected through a screw thread tightly
It is thickly set in the rear end of clamp part and the rear end of cannula part will be closely pressed in pressure-measuring pipe nozzle between the two.
2. a kind of device stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure according to claim 1, special
Sign is：Venthole on the pressure-measuring pipe nozzle is the pre-large post-small stepped hole of diameter, and the macropore of front end is included for cannula part
The outer diameter closely inserted, the diameter of the aperture of rear end are identical with the aperture of air intake duct.
3. a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure is fixed on benefit including stagnation pressure tube and by the stagnation pressure seal of tube
The pressure measurement seat in room housing is fired, stagnation pressure tube includes intubation mounting hole of the front end by corresponding perforation in afterburning room housing and pressure measurement seat
It stretches into the cannula part of afterburning chamber enclosure interior and is connected in the pressure-measuring pipe nozzle of cannula part rear end, the outer diameter of the pressure-measuring pipe nozzle
More than the diameter of intubation mounting hole；Extension, both ends along its length are provided in the middle part of cannula part and penetrate through the intubation portion
Point air intake duct, the entrance of the front end of air intake duct towards direction of flow, be provided in the middle part of pressure-measuring pipe nozzle with after the air intake duct
The connected venthole in end；It is characterized in that：The cannula part is Split type structure with pressure-measuring pipe nozzle, and cannula part is axis before
The straight-bar and its outer diameter of rear direction extension are less than the aperture of the intubation mounting hole so that it can be fully inserted into afterburning room housing
Portion, the pressure-measuring pipe nozzle are removably sealedly connected on the rear end of cannula part by connector, and the connector includes passing through
It clamp part that the installation through-hole at middle part is set on cannula part, the locking member that clamp part is fixed on cannula part and will survey
Pressure pipe nozzle is fixed on the pressure cap on clamp part；The clamp part is rear big preceding small waney body, and the forepart of clamp part leads to
The corresponding position that the locking member is fixed on cannula part is crossed, fluted, the pressure-measuring pipe is opened up in the middle part of the rear end of clamp part
Nozzle is mounted in the groove with being partially submerged into, and the pressure cap is connected through a screw thread the rear end for being closely set in clamp part and will locate
Pressure-measuring pipe nozzle between the two is closely pressed on the rear end of cannula part.
4. a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure according to claim 3, it is characterised in that：Institute
The venthole on pressure-measuring pipe nozzle is stated as the pre-large post-small stepped hole of diameter, the macropore of front end includes what is closely inserted for cannula part
Outer diameter, the diameter of the aperture of rear end are identical with the aperture of air intake duct.
5. a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure according to claim 3 or 4, feature exist
In：The clamp part includes the cone section with interior receipts inclined surface of forepart, circumferentially spaced in the cone section to offer at least two
Along pressure pipe part length direction extend gap, the gap in the axial direction front opening back-end closure, on the radial run through institute
The wall thickness of clamp part is stated, which, which to bore in section, forms the fingertip that can radially elasticly actuate；The locking member is to be arranged
Locking nut in the cone section, the forepart of locking nut are equipped with the inclined surface identical with the gradient of the cone section, revolve backward
Fingertip clamps cannula part to contract when twisting locking nut, so as to fulfill the fixation to cannula part.
6. a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure according to claim 5, it is characterised in that：Institute
It states and airtight and watertight padding is filled between pressure-measuring pipe nozzle and cannula part to ensure the sealing effect between cannula part and clamp part.
7. a kind of device for the test of Ducted rocket afterburning chamber stagnation pressure according to claim 6, it is characterised in that：Institute
The copper washer that the semicircle gasket that stating sealing fixed seat includes mainly being mutually matched by two panels forms.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510788086.3A CN105319069B (en) | 2015-11-17 | 2015-11-17 | A kind of device and its stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure |
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| CN201510788086.3A CN105319069B (en) | 2015-11-17 | 2015-11-17 | A kind of device and its stagnation pressure tube for the test of Ducted rocket afterburning chamber stagnation pressure |
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| CN109387370B (en) * | 2018-11-14 | 2023-12-22 | 中国空空导弹研究院 | Direct-connection type high-altitude simulation test axial force-free air inlet system of ramjet engine |
| CN109596361A (en) * | 2018-12-16 | 2019-04-09 | 中国航发沈阳发动机研究所 | Pressure-measuring pipe installation method and engine complete machine combustor exit stagnation pressure test suite |
| CN111122333B (en) * | 2019-12-06 | 2022-07-08 | 武汉航空仪表有限责任公司 | Multifunctional probe total pressure pipe pressurizing device |
| CN112729839B (en) * | 2020-12-15 | 2022-11-11 | 北京动力机械研究所 | Combustion measurement structure under large gas flow using condition |
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| CN203551188U (en) * | 2013-11-14 | 2014-04-16 | 无锡市鑫盛换热器制造有限公司 | Loosening prevention locking pressure test joint |
| CN204373690U (en) * | 2015-01-13 | 2015-06-03 | 西安远方航空技术发展总公司 | A kind of stagnation temperature total pressure measure apparatus |
| CN204461672U (en) * | 2015-03-13 | 2015-07-08 | 中航商用航空发动机有限责任公司 | The total compression testing device of a kind of pipeline |
| CN205262751U (en) * | 2015-11-17 | 2016-05-25 | 中国空空导弹研究院 | A device for consolidating always press test towards engine after burning room and total pipe of pressing thereof |
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2015
- 2015-11-17 CN CN201510788086.3A patent/CN105319069B/en active Active
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