CN107588939A - A kind of test tool of direct current centrifugation two-component injector element - Google Patents
A kind of test tool of direct current centrifugation two-component injector element Download PDFInfo
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- CN107588939A CN107588939A CN201710810636.6A CN201710810636A CN107588939A CN 107588939 A CN107588939 A CN 107588939A CN 201710810636 A CN201710810636 A CN 201710810636A CN 107588939 A CN107588939 A CN 107588939A
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Abstract
The present invention provides a kind of test tool of direct current centrifugation two-component injector element, from left to right includes gaseous oxidant chamber, liquid fuel liquid collecting chamber and the back-pressure chamber detachably connected successively；Liquid fuel liquid collecting chamber is provided with the conical through-hole of left and right extension, conical through-hole connection liquid fuel liquid collecting chamber and back-pressure chamber；Internal diameter is more than right side internal diameter on the left of conical through-hole；Nozzle interference fit is installed in conical through-hole, the inner chamber connection gaseous oxidant chamber and back-pressure chamber of nozzle, the helicla flute connection liquid fuel liquid collecting chamber and back-pressure chamber of nozzle.The test tool of the present invention, test nozzle and main jet directly can be tested and demarcated simultaneously, ensure that the structural integrity of two kinds of nozzles；Conical through-hole can realize the interference fit of nozzle and liquid fuel liquid collecting chamber, meet seal request on the premise of machining accuracy is reduced.The liquid fuel liquid collecting chamber of different development lengths can be selected on request simultaneously, to meet the test requirements document of different size nozzle.
Description
Technical field
The present invention relates to Aero-Space technical field of engines, more particularly to a kind of examination of direct current-centrifugation two-component injector element
Test frock.
Background technology
In the design and test process of Aero-Space engine, in order to improve test accuracy and test efficiency, it can not keep away
Need to use various test tools with exempting from.Wherein, the atomization experiment of engine nozzle is important in engine test
One ring, therefore the design of nozzle test frock and selection just seem particularly critical.
Generally, the nozzle for a kind of engine fuel being carried out to atomization process is referred to simply as " single-element injector ", and by two kinds
The nozzle that engine fuel carries out atomization process is referred to as " two-component injector element ".Nozzle in this test tool, neutral straight are led to
Road is the runner of oxidant, and oxygen supply agent " direct current " passes through；The helicla flute of outer ring surface is the passage of liquid propellant, and liquid is pushed away
Entering agent has certain " centrifugation " effect.
In conventional art and technique, the test tool of " single-element injector " can be used for the discharge coefficient of measure nozzle, examine
The blending of nozzle and atomizing effect, support is provided for the further igniting of analysis liquid-propellant rocket engine, combustion conditions.Current
" single-element injector " test tool is typically made up of nozzle, cavity body structure and back-pressure chamber etc..
And for " direct current-centrifugation two-component injector element ", to make the gap between nozzle and mounting seat meet seal request,
Need to propose machining accuracy higher requirement when designing using common nozzle and test tool, be difficult on design and processes
Realize.
In general " single-element injector " test tool is generally by measuring in the pressure and back pressure chamber room at nozzle entrance
Pressure obtains the pressure of nozzle, and can not obtain liquid propellant in helicla flute for " direct current-centrifugation two-component injector element "
Pressure drop.
In addition, in general " single-element injector " test tool is to realize that convenient disassembly ensures to seal again, in test tool
The difference in structure with the nozzle in engine head often be present in nozzle；And for needing to study many factors multiple combinations knot
Influence of the structure for nozzle performance, the nozzle that test unit often devises a variety of different types and size are tested respectively,
The nozzle quantity for resulting in the need for processing is huge, and material and cost of labor are higher.
The content of the invention
It is an object of the invention to provide a kind of test tool of direct current-centrifugation two-component injector element, to solve prior art
The seal request present in the experiment of nozzle is difficult to meet, nozzle can not repeat dismounting experiment, pressure drop is difficult to measure, material into
The problems such as this is high, test tool applicability is inadequate.
To achieve these goals, the present invention uses following technical scheme：
A kind of test tool of direct current-centrifugation two-component injector element provided by the invention, from left to right includes gas oxygen successively
Agent chamber, liquid fuel liquid collecting chamber and back-pressure chamber；The gaseous oxidant chamber, the liquid fuel liquid collecting chamber and
The back-pressure chamber detachably connects successively；The liquid fuel liquid collecting chamber is provided with the conical through-hole of left and right extension, described
Conical through-hole connects the liquid fuel liquid collecting chamber and the back-pressure chamber；Internal diameter is more than in right side on the left of the conical through-hole
Footpath；Direct current-centrifugation two-component injector element interference fit is installed in the conical through-hole, the inner chamber of direct current-centrifugation two-component injector element
The gaseous oxidant chamber and the back-pressure chamber are connected, the helicla flute of direct current-centrifugation two-component injector element connects the liquid
Fuel liquid collecting chamber and the back-pressure chamber.
Further, the test tool of direct current-centrifugation two-component injector element also includes the first pressure measuring mechanism and the second pressure measuring mechanism；
First pressure measuring mechanism is arranged at the inwall of the conical through-hole, and second pressure measuring mechanism is arranged at the back-pressure chamber
Inwall.The technical scheme has technical effect that：First pressure measuring mechanism is used to measure liquid propellant in helicla flute exit
Pressure, the second pressure measuring mechanism are used to measure the pressure of liquid propellant and gas propellant mixture matter in back-pressure chamber, entered
And accurately obtain the direct current-pressure drop of centrifugation two-component injector element in the course of the work.
Further, first pressure measuring mechanism and second pressure measuring mechanism include pressure sensor.The technical scheme
Have technical effect that：Due to activity space between helicla flute and conical through-hole inwall be present, and on back-pressure chamber inner wall similarly
The pressure sensor of settable thin slice, therefore pressure sensor directly can be fixedly installed in side wall, to obtain two positions rapidly
Pressure value.
Further, first pressure measuring mechanism and second pressure measuring mechanism include pressure measurement through hole and pressure sensor；
The conical through-hole connects with the pressure measurement through hole, and the pressure sensor can measure the taper by the pressure measurement through hole
Pressure in through hole；The back-pressure chamber connects with the pressure measurement through hole, and the pressure sensor passes through the pressure measurement through hole energy
Enough measure the pressure in the back pressure chamber room.The technical scheme has technical effect that：In order to obtain well-to-do installing space
And measurement space, pressure measurement through hole is respectively provided with the side wall of conical through-hole and back-pressure chamber, and set and press in pressure measurement through hole end
Force measurement device, the pressure value of two opening positions can be similarly obtained rapidly.
Further, the quantity of first pressure measuring mechanism is multiple that multiple first pressure measuring mechanisms lead to along the taper
The circumference in hole is uniformly distributed；The quantity of second pressure measuring mechanism is multiple, and multiple second pressure measuring mechanisms are along the back-pressure
The circumference of chamber is uniformly distributed.The technical scheme has technical effect that：Circumferentially it is uniformly distributed in the first of conical through-hole side wall
Pressure measuring mechanism, the second pressure measuring mechanism of back-pressure chamber sidewall is circumferentially uniformly distributed in, beneficial to observation direct current-centrifugation two-component injector element
Atomizing effect.
Further, the test tool of direct current-centrifugation two-component injector element also include the first seal assembly, the second seal assembly and
3rd seal assembly；First seal assembly be arranged at the gaseous oxidant chamber and the liquid fuel liquid collecting chamber it
Between, second seal assembly is arranged in the conical through-hole, and the 3rd seal assembly is arranged at the liquid fuel collection
Between sap cavity room and the back-pressure chamber.The technical scheme has technical effect that：Seal assembly is to realize gas oxygen
Between agent chamber and liquid fuel liquid collecting chamber, three seal isolation between cavity and exterior space, with improve pressure drop survey
The accuracy rate of amount, accurately obtain the result of the test of direct current-centrifugation two-component injector element.
Further, first seal assembly includes the first bulge loop, the first annular groove and the first packing ring；First bulge loop is set
Its right end face of the gaseous oxidant chamber is placed in, first annular groove is arranged at the left side of the liquid fuel liquid collecting chamber
End face, first bulge loop are built in first annular groove with first packing ring.The technique effect of the technical scheme exists
In：First bulge loop, which coincide, to be connected in the first annular groove, also, is set between the top end face of the first bulge loop and the bottom of the first annular groove
The first packing ring is put, meanwhile, the first packing ring and the first annular groove are interference fitted, and are greatly improved gaseous oxidant chamber and exterior space
Between seal isolation.
Further, second seal assembly includes second packing ring；The second packing ring interference fit is installed on the cone
Between the outer wall of inwall and direct current-centrifugation two-component injector element of shape through hole.The technical scheme has technical effect that：Due to taper
Through hole is mutually socketed with direct current-centrifugation two-component injector element, therefore second packing ring uses ring washer, and interference fit is installed on taper and led to
Between the outer wall of inwall and direct current-the centrifugation two-component injector element in hole, it can reliably ensure that gaseous oxidant chamber fires with liquid
Expect the pressure isolation between liquid collecting chamber.
Further, the 3rd seal assembly includes the 3rd bulge loop, the 3rd annular groove and the 3rd packing ring；3rd bulge loop is set
Its right end face of the liquid fuel liquid collecting chamber is placed in, the 3rd annular groove is arranged at the left end face of the back-pressure chamber,
3rd bulge loop is built in the 3rd annular groove with the 3rd packing ring.The technical scheme has technical effect that：The
Three bulge loops, which coincide, to be connected in the 3rd annular groove, also, sets between the top end face of the 3rd bulge loop and the bottom of the 3rd annular groove the
Three packing rings, meanwhile, the 3rd packing ring and the 3rd annular groove are interference fitted, the sealing being greatly improved between back-pressure chamber and exterior space
Isolation effect.
Further, the test tool of direct current-centrifugation two-component injector element also includes support ring, and the support ring is arranged at described
In gaseous oxidant chamber, left side abuts the side wall of the gaseous oxidant chamber, and right side abuts direct current-centrifugation two-component injector element
Left side.The technical scheme has technical effect that：Support ring is used to fix direct current-centrifugation two-component injector element, and improves
Direct current-centrifugation two-component injector element and conical through-hole sealing effectiveness.
The beneficial effects of the invention are as follows：
1st, because gaseous oxidant chamber, liquid fuel liquid collecting chamber detachably connect with back-pressure chamber, make to be tested directly
Dismounting test can be repeated several times in stream-centrifugation two-component injector element, test nozzle and main jet directly can be carried out simultaneously test with
Demarcation, ensure that the structural integrity of two kinds of nozzles.
2nd, the interference fit of direct current-centrifugation two-component injector element and liquid fuel liquid collecting chamber is realized using conical through-hole,
Meet the seal request of test tool on the premise of reducing machining accuracy.
3rd, the liquid fuel liquid collecting chamber of different development lengths can be selected on request, to meet different size direct current-centrifugation
The test requirements document of two-component injector element, reduce the construction cost of tooling device.
Brief description of the drawings
In order to illustrate more clearly of the technical scheme of the specific embodiment of the invention, embodiment will be described below
In the required accompanying drawing used be briefly described.It should be evident that drawings in the following description are some implementations of the present invention
Mode, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is the front view of the test tool of direct current provided in an embodiment of the present invention-centrifugation two-component injector element；
Fig. 2 is A-A direction views in Fig. 1；
Fig. 3 is B-B direction view in Fig. 1；
Fig. 4 is the partial enlarged drawing at I in Fig. 2；
Fig. 5 is the partial enlarged drawing at K in Fig. 2；
Fig. 6 is the partial enlarged drawing at N in Fig. 3；
Fig. 7 is direct current-centrifugation two-component injector element structural representation；
Fig. 8 is C-C direction views in Fig. 7.
Reference：
1- gaseous oxidant chambers；2- liquid fuel liquid collecting chambers；3- back-pressure chambers；
4- conical through-holes；5- direct currents-centrifugation two-component injector element；6- pressure measurement through holes；
The bulge loops of 7- first；The annular grooves of 8- first；The packing rings of 9- first；
10- second packing rings；The bulge loops of 11- the 3rd；The annular grooves of 12- the 3rd；
The packing rings of 13- the 3rd；14- support rings.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than instruction or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that instruction or hint relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, with concrete condition above-mentioned term can be understood at this
Concrete meaning in invention.
DESCRIPTION OF THE PRIOR ART：
In conventional art and technique, the test tool of " single-element injector " can be used for the discharge coefficient of measure nozzle, examine
The blending of nozzle and atomizing effect, support is provided for the further igniting of analysis liquid-propellant rocket engine, combustion conditions.Current
" single-element injector " test tool is typically made up of nozzle, cavity body structure and back-pressure chamber 3 etc..
And for " direct current-centrifugation two-component injector element 5 ", to make the gap between nozzle and mounting seat meet that sealing will
Ask, need to propose machining accuracy higher requirement when designing using common nozzle and test tool, on design and processes
It is difficult to.
In general " single-element injector " test tool is generally by measuring in the pressure and back-pressure chamber 3 at nozzle entrance
Pressure obtains the pressure of nozzle, and for " direct current-centrifugation two-component injector element 5 " can not obtain liquid propellant in helicla flute
Pressure drop.
In addition, in general " single-element injector " test tool is to realize that convenient disassembly ensures to seal again, in test tool
The difference in structure with the nozzle in engine head often be present in nozzle；And for needing to study many factors multiple combinations knot
Influence of the structure for nozzle performance, the nozzle that test unit often devises a variety of different types and size are tested respectively,
The nozzle quantity for resulting in the need for processing is huge, and material and cost of labor are higher.
The specific embodiment of the invention：
A kind of test tool of direct current-centrifugation two-component injector element 5 is present embodiments provided, wherein：Fig. 1 is implemented for the present invention
The front view of the test tool for direct current-centrifugation two-component injector element 5 that example provides；Fig. 2 is A-A direction views in Fig. 1；Fig. 3 is in Fig. 1
B-B direction view.As shown in Figures 1 to 3, the test tool of direct current-centrifugation two-component injector element 5 from left to right includes gas oxidation successively
Agent chamber 1, liquid fuel liquid collecting chamber 2 and back-pressure chamber 3.Specifically, gaseous oxidant chamber 1, liquid fuel liquid collecting chamber 2
Detachably connected successively with back-pressure chamber 3.Wherein, liquid fuel liquid collecting chamber 2 is provided with the conical through-hole 4 of left and right extension, cone
Shape through hole 4 connects liquid fuel liquid collecting chamber 2 and back-pressure chamber 3, and the left side internal diameter of conical through-hole 4 is more than right side internal diameter.Will be straight
Stream-interference fit of centrifugation two-component injector element 5 is installed in conical through-hole 4, the inner chamber connection gas of direct current-centrifugation two-component injector element 5
Body oxidant chamber 1 and back-pressure chamber 3, the He of helicla flute connection liquid fuel liquid collecting chamber 2 of direct current-centrifugation two-component injector element 5
Back-pressure chamber 3.During experiment, gaseous oxidant chamber 1 imports the gaseous propellant of high pressure, liquid fuel liquid collecting chamber 2
Import the liquid propellant of high pressure.On the premise of respective cavity meets air-proof condition, gaseous propellant is from the double groups of direct current-centrifugation
The center of first nozzle 5 enters back-pressure chamber 3, and liquid propellant enters back-pressure chamber 3 from helicla flute, by measuring and observing,
Complete the development test of direct current-centrifugation two-component injector element 5.
The test tool of direct current provided by the invention-centrifugation two-component injector element 5, can preferably solve prior art and spray
Seal request present in the experiment of mouth is difficult to meet, nozzle can not repeat dismounting experiment, pressure drop is difficult to measure, high processing costs
High, the problems such as test tool applicability is inadequate.Firstly, since gaseous oxidant chamber 1, liquid fuel liquid collecting chamber 2 and back-pressure
Chamber 3 is detachably connected, and dismounting test can be repeated several times by making to be tested direct current-centrifugation two-component injector element 5, and experiment can be sprayed simultaneously
Mouth and main jet are directly tested and demarcated, and ensure that the structural integrity of two kinds of nozzles.Secondly, conical through-hole 4 is utilized
The interference fit of direct current-centrifugation two-component injector element 5 and liquid fuel liquid collecting chamber 2 is realized, on the premise of machining accuracy is reduced
Meet the seal request of test tool.Again, the liquid fuel liquid collecting chamber 2 of different development lengths can be selected on request, with full
The test requirements document of sufficient different size direct current-centrifugation two-component injector element 5, reduce the construction cost of tooling device.
On the basis of above-described embodiment, further, the test tool of direct current-centrifugation two-component injector element 5 is additionally provided with
First pressure measuring mechanism and the second pressure measuring mechanism.Specifically, the first pressure measuring mechanism is arranged at the inwall of conical through-hole 4, the second pressure measurement
Mechanism is arranged at the inwall of back-pressure chamber 3.Wherein, the first pressure measuring mechanism is used to measure liquid propellant in helicla flute exit
Pressure, the second pressure measuring mechanism are used to measure the pressure of liquid propellant and gas propellant mixture matter in back-pressure chamber 3, entered
And accurately obtain the direct current-pressure drop of centrifugation two-component injector element 5 in the course of the work.
On the basis of above-described embodiment, further, the first pressure measuring mechanism and the second pressure measuring mechanism include pressure sensing
Device (does not mark).Due to activity space be present between helicla flute and the inwall of conical through-hole 4, and on the inwall of back-pressure chamber 3 similarly
Settable pressure sensor, therefore pressure sensor directly can be fixedly installed in side wall, to obtain the pressure of two positions rapidly
Value.
As shown in figure 3, on the basis of above-described embodiment, further, the first pressure measuring mechanism and the second pressure measuring mechanism are equal
Including pressure measurement through hole 6 and pressure sensor.Specifically, conical through-hole 4 connects with pressure measurement through hole 6, and pressure sensor passes through pressure measurement
Through hole 6 can measure the pressure in conical through-hole 4；Meanwhile back-pressure chamber 3 connects with pressure measurement through hole 6, pressure sensor passes through survey
Pressure through hole 6 can measure the pressure in back-pressure chamber 3.The test tool of the direct current of the present embodiment-centrifugation two-component injector element 5, it is
Well-to-do installing space and measurement space are obtained, pressure measurement through hole is respectively provided with the side wall of conical through-hole 4 and back-pressure chamber 3
6, and pressometer is set in the end of pressure measurement through hole 6, the pressure value of two opening positions can be similarly obtained rapidly.
On the basis of above-described embodiment, further, the quantity of the first pressure measuring mechanism is multiple, multiple first pressure measuring machines
Circumference of the structure along conical through-hole 4 is uniformly distributed；Likewise, the quantity of the second pressure measuring mechanism is multiple, multiple second pressure measuring mechanisms
It is uniformly distributed along the circumference of back-pressure chamber 3.It is circumferential equal in the test tool of the direct current-centrifugation two-component injector element 5 of the present embodiment
Even the first pressure measuring mechanism for being distributed in the side wall of conical through-hole 4, and circumferential the second pressure measurement for being uniformly distributed in the side wall of back-pressure chamber 3
Mechanism, it is more favorable for observing the atomizing effect of direct current-centrifugation two-component injector element 5.
On the basis of above-described embodiment, further, the test tool of direct current-centrifugation two-component injector element 5 is additionally provided with
First seal assembly, the second seal assembly and the 3rd seal assembly.Specifically, the first seal assembly is arranged at gaseous oxidant chamber
Between room 1 and liquid fuel liquid collecting chamber 2, the second seal assembly is arranged in conical through-hole 4, and the 3rd seal assembly is arranged at liquid
Between fluid fuel liquid collecting chamber 2 and back-pressure chamber 3.In the test tool of the direct current-centrifugation two-component injector element 5 of the present embodiment,
Seal assembly be in order to realize between gaseous oxidant chamber 1 and liquid fuel liquid collecting chamber 2, three cavitys and exterior space
Between seal isolation, to improve the accuracy rate of drop measurement, accurately obtain direct current-centrifugation two-component injector element 5 result of the test.
Fig. 4 is the partial enlarged drawing at I in Fig. 2, as shown in Figure 2,4, on the basis of above-described embodiment, and further,
First seal assembly includes the first bulge loop 7, the first annular groove 8 and the first packing ring 9.Specifically, the first bulge loop 7 is arranged at gas oxidation
Its right end face of agent chamber 1, the first annular groove 8 is arranged at the left end face of liquid fuel liquid collecting chamber 2, after installation, the first bulge loop 7
It is built in the first annular groove 8 with the first packing ring 9.In the test tool of the direct current-centrifugation two-component injector element 5 of the present embodiment,
First bulge loop 7, which coincide, to be connected in the first annular groove 8, also, between the top end face of the first bulge loop 7 and the bottom of the first annular groove 8
First packing ring 9 is set, meanwhile, the first packing ring 9 is interference fitted with the first annular groove 8, be greatly improved gaseous oxidant chamber 1 with it is outer
Seal isolation between portion space.
Fig. 6 is the partial enlarged drawing at N in Fig. 3, as shown in Fig. 3,6, on the basis of above-described embodiment, further,
Second seal assembly includes second packing ring 10, and second packing ring 10 be interference fitted be installed on the inwall of conical through-hole 4 and direct current-from
Between the outer wall of heart two-component injector element 5.In the test tool of the direct current-centrifugation two-component injector element 5 of the present embodiment, due to taper
Through hole 4 is mutually socketed with direct current-centrifugation two-component injector element 5, therefore second packing ring 10 uses ring washer, and interference fit is installed on cone
Between the outer wall of inwall and direct current-centrifugation two-component injector element 5 of shape through hole 4, can reliably ensure gaseous oxidant chamber 1 with
Pressure isolation between liquid fuel liquid collecting chamber 2.
Fig. 5 is the partial enlarged drawing at K in Fig. 2, as shown in Fig. 2,5, on the basis of above-described embodiment, further,
3rd seal assembly includes the 3rd bulge loop 11, the 3rd annular groove 12 and the 3rd packing ring 13.Specifically, the 3rd bulge loop 11 is arranged at liquid
Its right end face of fuel liquid collecting chamber 2, the 3rd annular groove 12 is arranged at the left end face of back-pressure chamber 3, after installation, the 3rd bulge loop 11
It is built in the 3rd annular groove 12 with the 3rd packing ring 13.In the test tool of the direct current-centrifugation two-component injector element 5 of the present embodiment
In, the 3rd bulge loop 11, which coincide, to be connected in the 3rd annular groove 12, also, at the top end face of the 3rd bulge loop 11 and the bottom of the 3rd annular groove 12
3rd packing ring 13 is set between portion, meanwhile, the 3rd packing ring 13 is interference fitted with the 3rd annular groove 12, is greatly improved back-pressure chamber 3
Seal isolation effect between exterior space.
As shown in Figure 2,3, on the basis of above-described embodiment, further, the experiment of direct current-centrifugation two-component injector element 5
Frock is additionally provided with support ring 14, and the support ring 14 is arranged in gaseous oxidant chamber 1, and its left side abuts gaseous oxidant chamber
The side wall of room 1, its right side abut the left side of direct current-centrifugation two-component injector element 5.Wherein, support ring 14 be used for fix direct current-from
Heart two-component injector element 5, and improve direct current-centrifugation two-component injector element 5 and the sealing effectiveness of conical through-hole 4.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, either which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
1. the test tool of a kind of direct current-centrifugation two-component injector element, it is characterised in that from left to right include gaseous oxidant successively
Chamber, liquid fuel liquid collecting chamber and back-pressure chamber；
The gaseous oxidant chamber, the liquid fuel liquid collecting chamber detachably connect successively with the back-pressure chamber；
The liquid fuel liquid collecting chamber is provided with the conical through-hole of left and right extension, and the conical through-hole connects the liquid fuel
Liquid collecting chamber and the back-pressure chamber；Internal diameter is more than right side internal diameter on the left of the conical through-hole；
Direct current-centrifugation two-component injector element interference fit is installed in the conical through-hole, the inner chamber of direct current-centrifugation two-component injector element
The gaseous oxidant chamber and the back-pressure chamber are connected, the helicla flute of direct current-centrifugation two-component injector element connects the liquid
Fuel liquid collecting chamber and the back-pressure chamber.
2. the test tool of direct current according to claim 1-centrifugation two-component injector element, it is characterised in that also including first
Pressure measuring mechanism and the second pressure measuring mechanism；First pressure measuring mechanism is arranged at the inwall of the conical through-hole, second pressure measurement
Mechanism is arranged at the inwall of the back-pressure chamber.
3. the test tool of direct current according to claim 2-centrifugation two-component injector element, it is characterised in that described first surveys
Press mechanism and second pressure measuring mechanism include pressure sensor.
4. the test tool of direct current according to claim 2-centrifugation two-component injector element, it is characterised in that described first surveys
Press mechanism and second pressure measuring mechanism include pressure measurement through hole and pressure sensor；
The conical through-hole is connected with the pressure measurement through hole, and the pressure sensor can be measured described by the pressure measurement through hole
Pressure in conical through-hole；
The back-pressure chamber is connected with the pressure measurement through hole, and the pressure sensor can be measured described by the pressure measurement through hole
Pressure in back pressure chamber room.
5. the test tool of direct current according to claim 2-centrifugation two-component injector element, it is characterised in that described first surveys
The quantity of press mechanism is multiple, and circumference of multiple first pressure measuring mechanisms along the conical through-hole is uniformly distributed；
The quantity of second pressure measuring mechanism is multiple, and circumference of multiple second pressure measuring mechanisms along the back-pressure chamber is uniformly
Distribution.
6. the test tool of direct current-centrifugation two-component injector element according to any one of Claims 1 to 5, it is characterised in that also
Including the first seal assembly, the second seal assembly and the 3rd seal assembly；First seal assembly is arranged at the gas oxygen
Between agent chamber and the liquid fuel liquid collecting chamber, second seal assembly is arranged in the conical through-hole, described
3rd seal assembly is arranged between the liquid fuel liquid collecting chamber and the back-pressure chamber.
7. the test tool of direct current according to claim 6-centrifugation two-component injector element, it is characterised in that described first is close
Sealing assembly includes the first bulge loop, the first annular groove and the first packing ring；
First bulge loop is arranged at its right end face of the gaseous oxidant chamber, and first annular groove is arranged at the liquid
The left end face of fuel liquid collecting chamber, first bulge loop are built in first annular groove with first packing ring.
8. the test tool of direct current according to claim 6-centrifugation two-component injector element, it is characterised in that described second is close
Sealing assembly includes second packing ring；
Second packing ring interference fit be installed on the inwall of the conical through-hole and direct current-centrifugation two-component injector element outer wall it
Between.
9. the test tool of direct current according to claim 6-centrifugation two-component injector element, it is characterised in that the described 3rd is close
Sealing assembly includes the 3rd bulge loop, the 3rd annular groove and the 3rd packing ring；
3rd bulge loop is arranged at its right end face of the liquid fuel liquid collecting chamber, and the 3rd annular groove is arranged at described anti-
The left end face of chamber is pressed, the 3rd bulge loop is built in the 3rd annular groove with the 3rd packing ring.
10. the test tool of direct current-centrifugation two-component injector element according to any one of Claims 1 to 5, it is characterised in that
Also include support ring, the support ring is arranged in the gaseous oxidant chamber, and left side abuts the gaseous oxidant chamber
Side wall, right side abut direct current-centrifugation two-component injector element left side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710810636.6A CN107588939A (en) | 2017-09-11 | 2017-09-11 | A kind of test tool of direct current centrifugation two-component injector element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710810636.6A CN107588939A (en) | 2017-09-11 | 2017-09-11 | A kind of test tool of direct current centrifugation two-component injector element |
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| Publication Number | Publication Date |
|---|---|
| CN107588939A true CN107588939A (en) | 2018-01-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710810636.6A Pending CN107588939A (en) | 2017-09-11 | 2017-09-11 | A kind of test tool of direct current centrifugation two-component injector element |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111766058A (en) * | 2020-07-31 | 2020-10-13 | 西安航天动力研究所 | Multi-interval double-gas-liquid coaxial centrifugal nozzle test device |
| CN111912614A (en) * | 2020-08-11 | 2020-11-10 | 江苏深蓝航天有限公司 | Centrifugal nozzle liquid flow test device of liquid rocket engine |
| CN112427232A (en) * | 2020-11-02 | 2021-03-02 | 宁波灵凡智远电子设备有限公司 | Continuous operation production line of double-component rotary mixed type dispensing robot |
| CN112557044A (en) * | 2020-11-25 | 2021-03-26 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101782029A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Device for testing flow characteristics of gas-gas nozzle |
| CN104895699A (en) * | 2015-04-28 | 2015-09-09 | 北京航空航天大学 | Small gas-gas injection optical transparent combustion device |
| CN105388007A (en) * | 2015-11-27 | 2016-03-09 | 北京航天动力研究所 | Combined removable nozzle test device |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN106089492A (en) * | 2016-07-01 | 2016-11-09 | 西安航天动力研究所 | A kind of ejector filler performance testing device |
| CN106601580A (en) * | 2015-10-19 | 2017-04-26 | 北京北方微电子基地设备工艺研究中心有限责任公司 | Air inlet mechanism and reaction cavity |
| CN106768908A (en) * | 2016-11-15 | 2017-05-31 | 中国航空动力机械研究所 | A kind of head can revolve nozzle spray characteristic test apparatus under the simulation operating mode of shifting |
-
2017
- 2017-09-11 CN CN201710810636.6A patent/CN107588939A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101782029A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Device for testing flow characteristics of gas-gas nozzle |
| CN104895699A (en) * | 2015-04-28 | 2015-09-09 | 北京航空航天大学 | Small gas-gas injection optical transparent combustion device |
| CN106601580A (en) * | 2015-10-19 | 2017-04-26 | 北京北方微电子基地设备工艺研究中心有限责任公司 | Air inlet mechanism and reaction cavity |
| CN105388007A (en) * | 2015-11-27 | 2016-03-09 | 北京航天动力研究所 | Combined removable nozzle test device |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN106089492A (en) * | 2016-07-01 | 2016-11-09 | 西安航天动力研究所 | A kind of ejector filler performance testing device |
| CN106768908A (en) * | 2016-11-15 | 2017-05-31 | 中国航空动力机械研究所 | A kind of head can revolve nozzle spray characteristic test apparatus under the simulation operating mode of shifting |
Non-Patent Citations (3)
| Title |
|---|
| 吴清: "《公差配合与检测》", 31 January 2013 * |
| 唐亮: "火箭发动机同轴式喷嘴雾化特性研究", 《中国优秀博硕士学位论文全文数据库 (硕士) 工程科技Ⅱ辑》 * |
| 金如山、索建秦著: "《先进燃气轮机燃烧室》", 31 August 2016 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111766058A (en) * | 2020-07-31 | 2020-10-13 | 西安航天动力研究所 | Multi-interval double-gas-liquid coaxial centrifugal nozzle test device |
| CN111766058B (en) * | 2020-07-31 | 2021-07-20 | 西安航天动力研究所 | Multi-interval double-gas-liquid coaxial centrifugal nozzle test device |
| CN111912614A (en) * | 2020-08-11 | 2020-11-10 | 江苏深蓝航天有限公司 | Centrifugal nozzle liquid flow test device of liquid rocket engine |
| CN112427232A (en) * | 2020-11-02 | 2021-03-02 | 宁波灵凡智远电子设备有限公司 | Continuous operation production line of double-component rotary mixed type dispensing robot |
| CN112557044A (en) * | 2020-11-25 | 2021-03-26 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
| CN112557044B (en) * | 2020-11-25 | 2021-11-02 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
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Application publication date: 20180116 |