CN210460894U

CN210460894U - Engine

Info

Publication number: CN210460894U
Application number: CN201921231006.4U
Authority: CN
Inventors: 不公告发明人
Original assignee: Ningbo Space Engine Technology Co ltd
Current assignee: Ningbo Space Engine Technology Co ltd
Priority date: 2019-07-31
Filing date: 2019-07-31
Publication date: 2020-05-05
Anticipated expiration: 2029-07-31

Abstract

The utility model discloses be suitable for the aircraft engine field, provide an engine. The utility model discloses an engine includes valve member, intercommunication valve member's combustion chamber and the spray tube of intercommunication combustion chamber. The combustion chamber comprises at least one first structural surface, and the first structural surface is a non-curved surface; the spray pipe comprises at least one second structural surface, the second structural surface is a non-curved surface, the first structural surface and the second structural surface are arranged in a one-to-one correspondence mode, and the first structural surface and the corresponding second structural surface are located on the same side of the engine. The embodiment of the utility model provides an in, through set up at least one for the first structural plane of non-curved surface in the combustion chamber, set up at least one for the second structural plane of non-curved surface at the spray tube, first structural plane and the setting of second structural plane one-to-one, first structural plane and the second structural plane that corresponds lie in the same one side of engine, in the limited inner space of aircraft, carry out the adaptability with the shape of engine according to the shape of finite space and design to reach the integration and the miniaturization of aircraft.

Description

Engine

Technical Field

The utility model belongs to the aircraft engine field especially relates to an engine.

Background

Generally, an aircraft mainly flies by virtue of the propulsive force generated by an orbit control engine, the orbit control engine has the characteristics of strong power, high performance, long service life, good combustion stability and repeated starting, reliable power can be provided for the aircraft such as a carrier rocket, a large satellite platform and an in-orbit service cabin, the task requirements of efficient orbit transfer, frequent in-orbit maneuvering and the like can be met, and the aircraft has good application potential and application space.

With the development of the aerospace industry, the demand for miniaturization and integration of the aircraft is higher and higher, and how to achieve the miniaturization, compactness, integration and the like of the internal functional components of the aircraft becomes a technology breakthrough point which is concerned more and more. However, the internal space of the aircraft is limited, the number of internal functional components is large, the structure is complex, and the connection relationship between the functional components is complex, so that the miniaturization and integration of the aircraft are affected.

In an aircraft system, the assembly of all functional components is completed on a limited spatial layout, and the layout of the whole aircraft needs to be optimized. However, after the layout of the aircraft is completed, it is often found that the remaining space does not conform to the existing shape of a certain functional component (such as an engine), and the layout and installation cannot be performed. In view of the above problems, the prior art generally implements complete layout of all functional modules by redesigning the aircraft, such as increasing the space and the total weight of the aircraft, which not only results in that the aircraft cannot meet the requirements of miniaturization and integration, but also increases the volume and the weight, affects the assembly of the aircraft, and increases the unnecessary workload and cost.

SUMMERY OF THE UTILITY MODEL

The utility model provides an engine aims at solving and carries out holistic installation overall arrangement back to the functional unit of aircraft, and the remaining inner space of aircraft does not accord with the current appearance of a certain subassembly, can't carry out the problem of overall arrangement installation.

The utility model discloses a realize like this, an engine, it includes:

a valve assembly;

a combustion chamber in communication with the valve assembly, the combustion chamber including at least one first structural surface, the first structural surface being a non-curved surface; and

the nozzle is communicated with the combustion chamber and comprises at least one second structural surface, the second structural surface is a non-curved surface, the first structural surface and the second structural surface are arranged in a one-to-one correspondence mode, and the first structural surface and the second structural surface which correspond to each other are located on the same side of the engine.

Furthermore, the number of the first structural surfaces and the number of the second structural surfaces are two, the two first structural surfaces and the two second structural surfaces are respectively and symmetrically arranged on two sides of the engine, the first structural surfaces are planes, the second structural surfaces are planes, and the first structural surfaces are parallel to the second structural surfaces.

Furthermore, the valve assembly comprises a rectangular shell and a control valve accommodated in the shell, the engine comprises a first pipeline and a second pipeline, the first pipeline and the second pipeline are arranged at one end of the shell far away from the combustion chamber in parallel, and the first pipeline and the second pipeline are both communicated with the control valve.

Furthermore, the valve assembly comprises two third structural surfaces respectively formed on two sides of the housing, and the third structural surface positioned on the same side of the engine and the first structural surface are positioned on the same plane.

Furthermore, the one end that the shell is close to the combustion chamber is equipped with first connecting portion, the one end that the combustion chamber is close to the shell is equipped with the second connecting portion, first connecting portion and second connecting portion are the flange, first connecting portion are equipped with a plurality of first screw, the second connecting portion are equipped with a plurality of second screw, the valve member with the combustion chamber is worn to establish through the screw first screw with the second screw is with fixed connection.

Still further, the engine further comprises an injector located within the combustion chamber and communicating the control valve with the combustion chamber, the injector comprising a first nozzle and a second nozzle, the control valve comprising a first control element and a second control element, the first control element communicating with the first nozzle and the second control element communicating with the second nozzle.

The utility model discloses the beneficial effect who reaches is, owing to set up at least one first structural plane for the non-curved surface at the combustion chamber, set up at least one second structural plane for the non-curved surface at the spray tube, first structural plane sets up with second structural plane one-to-one, first structural plane lies in same one side of engine with the second structural plane that corresponds, so in the integral erection process of the functional unit of aircraft, be special-shaped limited inner space's the condition under the aircraft, carry out the adaptability design with the shape of engine according to the shape of finite space, can solve the engine overall arrangement, the problem of installation, integration and miniaturization mesh with reaching the aircraft.

Drawings

Fig. 1 is a schematic perspective view of an engine according to an embodiment of the present invention;

FIG. 2 is a schematic structural view of a valve assembly according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a control valve provided in an embodiment of the present invention;

fig. 4 is a schematic structural diagram of an injector according to an embodiment of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

The embodiment of the utility model provides a owing to set up at least one first structural plane for the non-curved surface at the combustion chamber, set up at least one second structural plane for the non-curved surface at the spray tube, first structural plane sets up with second structural plane one-to-one, first structural plane lies in same one side of engine with the second structural plane that corresponds, so in the unit mount process of the functional unit of aircraft, be special-shaped limited inner space's the condition at the aircraft under, carry out the adaptability design with the shape of engine according to the shape of finite space, can solve the engine overall arrangement, the problem of installation, integration and miniaturization mesh with reaching the aircraft.

Example one

Referring to fig. 1, an engine 100 according to an embodiment of the present invention includes a valve assembly 10, a combustion chamber 20 communicating with the valve assembly 10, and a nozzle 30 communicating with the combustion chamber 20. The combustion chamber 20 includes at least one first structural surface 21, the first structural surface 21 being a non-curved surface. The nozzle 30 includes at least one second structural surface 31, the second structural surface 31 is a non-curved surface, the first structural surface 21 and the second structural surface 31 are disposed in a one-to-one correspondence, and the first structural surface 21 and the corresponding second structural surface 31 are located on the same side of the engine 100.

The embodiment of the utility model provides a set up at least one first structural plane 21 for the non-curved surface at combustion chamber 20, set up at least one second structural plane 31 for the non-curved surface at spray tube 30, first structural plane 21 sets up with second structural plane 31 one-to-one, first structural plane 21 lies in the same one side of engine 100 with the second structural plane 31 that corresponds, so in the integral erection process of the functional unit of aircraft, under the condition of special-shaped limited inner space, carry out the adaptability design with the shape of engine 100 according to the shape of finite space, can solve the overall arrangement of engine 100, the installation problem, with integration and the miniaturized mesh of reaching the aircraft.

Specifically, the engine 100 of the present invention is an orbital engine 100, the engine 100 is a main power source of the aircraft, the engine 100 can be connected to a storage tank of the aircraft and can be connected with fuel, etc., the combustion chamber 20 is a hollow cavity structure, the fuel can be atomized, mixed and combusted in the combustion chamber 20 to react and form high-temperature fuel gas, so as to generate power, so that the aircraft moves in a predetermined direction, generally, the jet direction of the engine 100 (i.e., the opening direction of the nozzle 30) is opposite to the forward direction of the aircraft, and thus the forward direction of the aircraft can be confirmed by directly passing through the position orientation of the engine 100.

The combustion chamber 20 is a hollow right cylindrical body with a processed cross section, the processed cross section of the combustion chamber 20 forms a first structural surface 21, and the first structural surface 21 extends from one end to the other end of the combustion chamber 20. The diameter of one end of the combustion chamber 20 close to the nozzle 30 is gradually reduced, the diameter of the nozzle reaches the minimum at the throat position of the engine 100, the diameter passing through the throat position is gradually expanded and increased and is communicated with the nozzle 30, the nozzle 30 is a Laval nozzle 30 and is in a circular truncated cone shape with cross section processing, the cross section processing part of the nozzle 30 forms a second structural surface 31, and the diameter of the nozzle 30 gradually extends and expands from one end close to the combustion chamber 20 to the other end. The space occupied by the curved surface is large, and the first structural surface 21 and the second structural surface 31 are both non-curved surfaces, so that part of the outer contour of the engine 100 is non-curved, and when the inner space of the engine 100 is abnormal and insufficient, part of the outer contour of the engine 100 is non-curved, the engine can adapt to the limited abnormal inner space of the aircraft, and the space utilization rate of the engine 100 is improved.

More, the non-curved surface can include the face that does not have the crooked radian such as plane, the face of buckling, and is comparatively regular pleasing to the eye, also can adapt to the limited dysmorphism inner space of aircraft better simultaneously, in more embodiments, the shape of first structural plane 21 and second structural plane 31 can also be other, under the prerequisite of the effective adaptation of the inner space of guaranteeing engine 100 to the aircraft, specifically set up can, do not do specific restriction here.

Example two

Referring to fig. 1, furthermore, the number of the first structural surfaces 21 and the second structural surfaces 31 is two, the two first structural surfaces 21 and the two second structural surfaces 31 are respectively symmetrically disposed on two sides of the engine 100, the first structural surface 21 is a plane, the second structural surface 31 is a plane, and the first structural surface 21 and the second structural surface 31 are parallel.

The number of the first structural surface 21 and the second structural surface 31 is two, which not only reserves enough internal reaction space of the combustion chamber 20 and the nozzle 30 to ensure enough power source of the engine 100, but also increases the area of the non-curved outer contour of the engine 100, and further meets the installation requirement when the internal special-shaped space of the aircraft is limited. The dotted line L is a line parallel to the central axis of the combustion chamber 20, and it can be understood that the two first structural surfaces 21 and the two second structural surfaces 31 are respectively symmetrically disposed on two sides of the engine 100, that is, the two first structural surfaces 21 are symmetrically disposed on a cross section parallel to the first structural surface 21 formed by the engine 100 with the dotted line L, and the two second structural surfaces 31 are symmetrically disposed on a cross section parallel to the second structural surface 31 formed by the engine 100 with the dotted line L, so that the appearance of the engine 100 is more beautiful and regular, and the adaptability of the engine 100 to the limited irregular space of the aircraft is further improved.

Of course, in more embodiments, the number of the first structural surface 21 and the second structural surface 31 may be one, and it is also possible to eliminate the first structural surface 21 and only the second structural surface 31, or eliminate the second structural surface 31 and only the first structural surface 21, so as to simplify the structure of the engine 100; in other embodiments, the number of the first structural surface 21 and the second structural surface 31 may also be three, four, or the like, or more, so as to further increase the non-curved outer contour area of the engine 100, and the number of the first structural surface 21 and the second structural surface 31 may also be unequal, and the above description of the first structural surface 21 and the second structural surface 31 is only an example, and may be specifically provided in a specific embodiment.

The first structural surface 21 and the second structural surface 31 are both planes, the planes are regular and beautiful, the setting difficulty is low, the production difficulty of the engine 100 is reduced, the first structural surface 21 and the second structural surface 31 are both planes and are parallel to each other, the engine can adapt to more inner spaces of aircrafts, and the adaptation degree of the engine 100 is improved. In further embodiments, the first structure surface 21 and the second structure surface 31 may be non-planar and not parallel to each other, and are not limited herein, and may be specifically configured in specific embodiments.

EXAMPLE III

Referring to fig. 1 and 2, in addition, the valve assembly 10 includes a rectangular housing 11 and a control valve 12 accommodated in the housing 11, the engine 100 includes a first pipe 13 and a second pipe 14, the first pipe 13 and the second pipe 14 are arranged in parallel at an end of the housing 11 away from the combustion chamber 20, and both the first pipe 13 and the second pipe 14 are communicated with the control valve 12.

Specifically, the housing 11 is substantially rectangular, which can further increase the non-curved surface area of the engine 100 and improve the adaptability of the engine 100 to the irregular space inside the aircraft. The control valve 12 is accommodated in the housing 11, and the housing 11 can better protect the control valve 12 from being damaged by the outside, thereby ensuring the service life of the control valve 12 and the normal operation of the engine 100. In the embodiment of the present invention, the first pipeline 13 and the second pipeline 14 are both communicated with the control valve 12, the first pipeline 13 is an oxidant pipeline, the first pipeline 13 is used for guiding the oxidant to the control valve 12 from the outside, the second pipeline 14 is a fuel pipeline, the second pipeline 14 is used for guiding the fuel to the control valve 12 from the outside, the control valve 12 can respectively control the supply and the closing of the oxidant and the fuel, and the oxidant and the fuel are transmitted to the subsequent structure, so as to ensure the normal power source of the engine 100 and the aircraft.

In further embodiments, the first pipe 13 is not limited to flowing an oxidant, and the second pipe 14 is not limited to flowing a fuel, for example, the first pipe 13 may also be a fuel pipe and used for flowing a fuel, and the second pipe 14 may also be an oxidant pipe and used for flowing an oxidant, which is not limited herein, and is specifically selected in the specific embodiment.

Example four

Referring to fig. 1, the valve assembly 10 further includes two third structural surfaces 111 respectively formed on two sides of the housing 11, and the third structural surface 111 located on the same side of the engine 100 is in the same plane as the first structural surface 21.

It can be understood that, since the housing 11 is rectangular, the third structural surface 111 is also a plane, the third structural surface 111 is connected to the first structural surface 21 and is located in the same plane, and the third structural surface 111 is also parallel to the second structural surface 31, so that the surface formed between the valve assembly 10 and the combustion chamber 20 is relatively flat, which is beneficial to increasing the non-curved surface area of the overall outer contour of the engine 100, and further improving the adaptability of the engine 100 to the aircraft when the internal irregular space of the aircraft is limited.

EXAMPLE five

Referring to fig. 1, furthermore, a first connecting portion 112 is disposed at an end of the casing 11 close to the combustion chamber 20, a second connecting portion 22 is disposed at an end of the combustion chamber 20 close to the casing 11, the first connecting portion 112 and the second connecting portion 22 are both flanges, the first connecting portion 112 is disposed with a plurality of first screw holes 113, the second connecting portion 22 is disposed with a plurality of second screw holes, and the valve assembly 10 and the combustion chamber 20 are fixedly connected by passing through the first screw holes 113 and the second screw holes by screws.

Specifically, the first connecting portion 112 is integrally formed with the housing 11, and the first connecting portion 112 is formed at an edge of the housing 11 close to the arc-shaped portion of the combustion chamber 20, is formed by extending outward from the edge, and is symmetrically formed at both sides of the housing 11; the second connection portion 22 is integrally formed with the combustion chamber 20, and the second connection portion 22 is formed at an edge of the combustion chamber 20 close to the arc portion of the housing 11, is formed by extending the edge outward, and is symmetrically formed at both sides of the combustion chamber 20. A flange pad may be added between the first connecting portion 112 and the second connecting portion 22, and during the assembly and production process of the engine 100, the first connecting portion 112 and the second connecting portion 22 are aligned first, and a plurality of screws respectively penetrate through a plurality of corresponding first screw holes 113 and a plurality of corresponding second screw holes, so as to fixedly connect the valve assembly 10 (the housing 11) and the combustion chamber 20. The connection mode between the first connection portion 112 and the second connection portion 22, that is, the mode of fixedly connecting the two flanges, is relatively convenient to implement, can bear relatively large pressure, and has relatively high stability when the aircraft operates at high speed and high pressure, thereby ensuring the safety and stability of the aircraft.

In further embodiments, the fixing manner of the first connection portion 112 and the second connection portion 22 is not limited to the screw fastening manner mentioned above, and may be fixed by welding, riveting, or the like, and may be specifically set in a specific real-time manner.

EXAMPLE six

Referring to fig. 1, 3 and 4, further, the engine 100 further includes an injector 40 located in the combustion chamber 20 and communicating the control valve 12 with the combustion chamber 20, the injector 40 includes a first nozzle 41 and a second nozzle 42, the control valve 12 includes a first control element 121 and a second control element 122, the first control element 121 communicates with the first nozzle 41, and the second control element 122 communicates with the second nozzle 42.

Specifically, in the embodiment of the present invention, the first control element 121 is an oxidant control valve, the second control element 122 is a fuel control valve, the first nozzle 41 is an oxidant nozzle, and the second nozzle 42 is a fuel nozzle. The oxidant and the fuel are respectively transmitted to the control valve 12 through the first pipe 13 and the second pipe 14, then guided to the injector 40, and finally injected into the combustion chamber 20 for reaction. Specifically, the first control element 121 and the second control element 122 respectively control the supply and the shut-off of the oxidant and the fuel, and when the first control element 121 and the second control element 122 are turned on, the oxidant and the fuel are respectively injected into the combustion chamber 20 through the first pipe 13 and the second pipe 14, the first control element 121 and the second control element 122, and the first nozzle 41 and the second nozzle 42, so as to perform mixed combustion, ignition and the like.

In further embodiments, the first control element 121 is not limited to an oxidant control valve, the first nozzle 41 is not limited to an oxidant nozzle, the second control element 122 is not limited to a fuel control valve, the second nozzle 42 is not limited to a fuel nozzle, the first control element 121 may also be a fuel control valve, the first nozzle 41 may also be a fuel nozzle, the second control element 122 may also be an oxidant control valve, and the second nozzle 42 may also be an oxidant nozzle, which is not limited specifically herein, and is selected specifically in practical embodiments.

The embodiment of the present invention provides a planar first structure surface 21 disposed in a combustion chamber 20, a planar second structure surface 31 disposed in a nozzle 30, the first structure surface 21 and the second structure surface 31 are two and disposed in a one-to-one correspondence, the first structure surface 21 and the corresponding second structure surface 31 are disposed at the same side of an engine 100 and are parallel to each other, a valve assembly 10 having a rectangular outer contour is further disposed, a third structure surface 111 of the valve assembly 10 is connected to the first structure surface 21 and is disposed at the same plane, and a first pipeline 13 and a second pipeline 14 are reasonably disposed in the valve assembly 10 to improve the space utilization rate of the engine 100, in the process of mounting the engine 100 to an aircraft, when the inside special-shaped space of the aircraft is limited, the shape of the engine 100 is adaptively designed with the shape of the inside special-shaped space, the layout of the engine 100 can be solved, Installation problems, improved engine 100 compatibility, and achieving integration and miniaturization of the aircraft.

The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims

1. An engine, comprising:

a valve assembly;

2. The engine of claim 1, wherein the first structural surface is planar and the second structural surface is planar, the first structural surface being parallel to the second structural surface;

the number of the first structural surfaces and the number of the second structural surfaces are two, and the two first structural surfaces and the two second structural surfaces are symmetrically arranged on two sides of the engine respectively.

3. The engine of claim 1, wherein the valve assembly comprises a rectangular housing and a control valve received in the housing, the engine comprising a first conduit and a second conduit, the first conduit and the second conduit being juxtaposed at an end of the housing remote from the combustion chamber, the first conduit and the second conduit both being in communication with the control valve.

4. The engine of claim 3, wherein said valve assembly includes two third structural surfaces formed on opposite sides of said housing, said third structural surfaces on the same side of said engine being coplanar with said first structural surface.

5. The engine according to claim 3, characterized in that a first connecting part is arranged at one end of the housing close to the combustion chamber, a second connecting part is arranged at one end of the combustion chamber close to the housing, the first connecting part and the second connecting part are both flanges, the first connecting part is provided with a plurality of first screw holes, the second connecting part is provided with a plurality of second screw holes, and the valve component and the combustion chamber are fixedly connected by passing screws through the first screw holes and the second screw holes.

6. The engine of claim 3, further comprising an injector positioned within said combustion chamber and in communication with said control valve and said combustion chamber, said injector comprising a first nozzle and a second nozzle, said control valve comprising a first control element and a second control element, said first control element in communication with said first nozzle and said second control element in communication with said second nozzle.