阅读说明：本技术 一种发动机隔热喷管 (Heat-insulating spray pipe of engine ) 是由 杨子仲 卞静 于静 于 2020-11-25 设计创作，主要内容包括：本申请提供了一种发动机隔热喷管,所述隔热喷管包括：多级的引射喷管,多级的引射喷管设置在发动机的尾部,整体上成逐渐的收缩状,相邻两个引射喷管之间具有预定的间隙,且在周向上通过点阵连接结构连接。本申请所提供发动机隔热喷管通过多级引射的方式将发动机舱内的冷气引射到喷管内,可以在喷管内形成冷气层,从而有效的降低喷管和发动机舱的温度,进而实现了对热防护区域的隔热效果。(The application provides an engine thermal-insulated spray tube, thermal-insulated spray tube includes: multistage injection spray pipes are arranged at the tail of the engine and gradually contracted integrally, a preset gap is reserved between every two adjacent injection spray pipes, and the two adjacent injection spray pipes are connected in the circumferential direction through a dot matrix connection structure. The application provides engine thermal-insulated spray tube penetrates the spray tube through the mode that multistage penetrates with the air conditioning in the engine compartment, can form cold gas layer in the spray tube to the effectual temperature that reduces spray tube and engine compartment, and then realized the thermal-insulated effect to hot protective area.)

1. An insulated engine nozzle, characterized in that the insulated nozzle (2) comprises: multistage injection spray pipe (21), multistage injection spray pipe (21) set up the afterbody at engine (1), become gradually shrink form on the whole, have predetermined clearance between two adjacent injection spray pipes, and connect through dot matrix connection structure (22) in circumference.

2. The engine insulating nozzle according to claim 1, characterized in that the number of stages of the ejector nozzle (21) is 3-5.

3. The insulated jet engine nozzle of claim 1, wherein the lattice-connecting structure (22) comprises at least one cellular structure formed by connecting bottom surfaces of polygonal pyramids that are symmetrical to each other.

4. The insulated jet engine nozzle according to any one of claims 1 to 3, characterized in that the ejector nozzle (21) and the lattice-connection structure (22) are manufactured by additive manufacturing.

5. The insulated jet engine nozzle of claim 4, wherein the jet nozzle (21) and the lattice-connecting structure (22) are made of the same material.

6. The insulated engine nozzle of claim 5, wherein the material comprises a metal, a metal alloy, or a high temperature resistant composite material.

7. The insulated engine nozzle of claim 1, wherein the pilot nozzle has a wave structure (211) at least partially from the distal end to the forward end in the axial direction.

8. The insulated jet engine nozzle of claim 1, wherein the gap between two adjacent jet nozzles (21) is not more than 5 mm.

Technical Field

The application belongs to the technical field of aeroengines, and particularly relates to an engine heat-insulation spray pipe.

Background

The engine is the necessary equipment that the aircraft needs, and all engines utilize chemical energy to produce the required power of aircraft flight at present. During the conversion process, the engine must dissipate heat to the surrounding space, with the nozzle being at its highest temperature and dissipating heat to the surrounding area the most. It is therefore important to provide the necessary thermal insulation to the lance.

In the prior art, annular channels are mostly adopted for spray pipe heat insulation, ambient air is ejected by spray pipe jet flow, and the air in the ambient air is used for heat insulation. The annular channel is composed of a spray pipe, an outer shell and a support column. The welding process is used for assembling and welding connection, and the problems of heavy weight, large deformation, complex shape, incapability of manufacturing and the like exist. Therefore, the heat insulation effect is general.

Disclosure of Invention

It is an object of the present application to provide an insulated engine nozzle that addresses or mitigates at least one of the problems of the background art.

The technical scheme of the application is as follows: an insulated engine nozzle, comprising: multistage injection spray pipes are arranged at the tail of the engine and gradually contracted integrally, a preset gap is reserved between every two adjacent injection spray pipes, and the two adjacent injection spray pipes are connected in the circumferential direction through a dot matrix connection structure.

Further, the lattice-connected structure includes at least one cell structure, and the cell structure is formed by connecting mutually symmetrical polygonal pyramids with bottom surfaces.

Furthermore, the injection nozzle and the dot matrix connecting structure are manufactured in an additive mode.

Furthermore, the injection nozzle and the lattice connection structure are made of the same material.

Further, the material comprises metal, metal alloy or high-temperature resistant composite material.

Furthermore, the gap between two adjacent injection nozzles is not more than 5 mm.

Furthermore, the number of stages of the injection spray pipe is 3-5.

Further, the injection nozzle is at least partially provided with a wave structure from the tail end to the front end along the axial direction.

The application provides engine thermal-insulated spray tube penetrates the spray tube through the mode that multistage penetrates with the air conditioning in the engine compartment, can form cold gas layer in the spray tube to the effectual temperature that reduces spray tube and engine compartment, and then realized the thermal-insulated effect to hot protective area.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic view of the installation position of the engine insulating nozzle of the present application.

FIG. 2 is a schematic diagram of an engine insulated nozzle according to the present application.

Fig. 3 is a schematic connection diagram of two adjacent ejector nozzles according to the present application.

FIG. 4 is a schematic view of a jet nozzle of the present application.

Reference numerals:

1-engines

2-Heat insulation spray pipe

21-jet ejector pipe, 211-wave structure,

22-lattice connecting structure

23-injection air flow

24-Cold air layer

25-main heat gas

3-aircraft structure

4-engine compartment

5-area of thermal protection

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to overcome the heat-insulating effect of the heat-insulated spraying pipe in the prior art poor, weight and the big scheduling problem of deformation, the application provides a novel engine heat-insulating spraying pipe that weight is little, heat-insulating effectual.

As shown in fig. 1 and 2, the heat-insulating nozzle 2 of the engine provided by the present application mainly includes a plurality of stages of ejector nozzles 21, a gap with a predetermined width is formed between two adjacent ejector nozzles 21, and the two adjacent ejector nozzles 21 are connected in the circumferential direction by a dot matrix connection structure 22, and the integral heat-insulating nozzle formed after the connection of the plurality of stages of ejector nozzles 21 is disposed behind the engine 1 and is in a shrinking shape as a whole. Through the form of multistage ejector nozzle, can be at engine 1 during operation, air conditioning in the engine compartment 4 forms bleed air current 23 and sprays to thermal-insulated spray tube 2 in, thereby can form cold gas layer 24 in thermal-insulated spray tube 2, cold gas layer 24 can be in the inboard of thermal-insulated spray tube 2 of the effectual main hot gas 25 of discharging engine 1 of ejector nozzle 21, and then the effectual temperature that reduces thermal-insulated spray tube 2 and engine compartment 4, the effective thermal-insulated of thermal protection zone 5 in the aircraft structure 4 has been realized.

In the application, the number of stages of the ejector nozzle 21 is usually not too many or too few, and preferably, the ejector nozzle 21 is 3-5 stages. For example, in the embodiment shown in fig. 2, the number of stages of the ejector nozzle 21 is 4, and the ejector nozzle 21a to 21d is provided.

It should be noted that, in order to improve the ejector effect, the ejector nozzle of the previous stage is at least partially covered by the ejector nozzle of the subsequent stage on the radial cross section.

Taking the example shown in fig. 3 that the ejector nozzles 21a and 21b are connected by the dot matrix connection structure 22, the connection between the adjacent ejector nozzles is the same, and the description is omitted. The lattice-connecting structure 22 generally comprises at least one cell structure, which is formed by polygonal pyramids symmetrical to each other and connected on the ground, and when there are a plurality of cell structures, the cell structures are connected on the tops of the polygonal pyramids. The lattice-connected structure 22 shown in fig. 3, for example, includes two cell structures, each cell structure is formed by connecting two symmetrical quadrangular pyramids with the ground, and the two cell structures are connected by the vertices of the quadrangular pyramids. It is understood that the quadrangular pyramid in the above embodiments may also be a trilateral or other polygonal shape.

In a manufacturing method that can realize the structure, the ejector nozzle 21 and the dot matrix connection structure 22 can be manufactured in an additive manufacturing method. Further, the ejector nozzle 21 and the dot matrix connection structure 22 are made of the same material. The material may include a metal material, a metal alloy material, or a high temperature resistant composite material.

As shown in fig. 4, which is a schematic structural diagram of the jet nozzle 21, a wavy structure 211 is formed on the jet nozzle 21, and the wavy structure 211 extends from the tail end of the jet nozzle 21 to the front end thereof (with reference to the airflow direction) in the axial direction of the jet nozzle 21. Wherein the wave structure 211 may occupy the entire width (i.e., axial direction), it may also occupy a proportion of the width. For example, in the illustration, the wave structures 211 occupy approximately 90% of the entire width.

Finally, the gap between two adjacent injection nozzles 21 is not too large, and preferably, the gap between two adjacent injection nozzles 21 is not more than 5 mm.

The utility model provides an engine heat insulation structure passes through lattice connection structure and connects multistage injection spray tube as a whole, makes the air current in the engine compartment jet out and form the cold air layer in can injecting the spray tube adjacent to protect thermal-insulated spray tube, and the annular passage between thermal-insulated spray tube and outside casing can form complicated air passage, further improves the heat exchange efficiency who injects the air, reaches the effect that promotes thermal-insulated effect.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.