阅读说明：本技术 液体火箭发动机推力室头部喷注器的多零件结构焊接方法 (Multi-part structure welding method for liquid rocket engine thrust chamber head injector ) 是由 李明刚 孙飞 于 2021-07-26 设计创作，主要内容包括：本发明公开了液体火箭发动机推力室头部喷注器的多零件结构焊接方法,其特征在于：具体包括以下步骤：S1、焊接前处理：首先通过数控设备在圆形底座下端面标刻若干个十字焊接基准,S2、清洗除杂,S3、装配,S4、焊接,S5、后处理本发明涉及航天设备加工技术领域。该液体火箭发动机推力室头部喷注器的多零件结构焊接方法,可实现将待焊接的喷头单元先进行整体装配至底座的焊接位置,再进行统一焊接处理,很好的达到了既快速又方便的进行焊接的目的,焊接方便,且焊接效率高,无需将多个待焊接的喷头单元与逐个的与固定底板上的喷孔进行装配对齐和焊接,操作简单,大大减轻了生产人员的劳动强度,大大方便了室头部喷注器的生产。(The invention discloses a method for welding a multi-part structure of a head injector of a thrust chamber of a liquid rocket engine, which is characterized by comprising the following steps of: the method specifically comprises the following steps: s1, pre-welding treatment: the method comprises the steps of marking a plurality of cross welding references on the lower end face of a circular base through numerical control equipment, S2, cleaning and removing impurities, S3, assembling, S4, welding, S5 and post-processing, and relates to the technical field of aerospace equipment processing. The method for welding the multi-part structure of the liquid rocket engine thrust chamber head injector can realize that the nozzle units to be welded are integrally assembled to the welding position of the base firstly and then are uniformly welded, the aim of quickly and conveniently welding is well achieved, the welding is convenient, the welding efficiency is high, the nozzle units to be welded are not required to be assembled, aligned and welded with the spray holes on the fixed base plate one by one, the operation is simple, the labor intensity of production personnel is greatly reduced, and the production of the chamber head injector is greatly facilitated.)

1. The method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine is characterized by comprising the following steps of: the method specifically comprises the following steps:

s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through numerical control equipment, and then machining and manufacturing a welding part through machining equipment according to the process size requirement of the head injector required by the actual requirement;

s2, cleaning and impurity removing: washing the base and the nozzle unit which are subjected to the standard carving and machining in the step S1 for 2-3 times by using clean water, then putting the washed base and the washed nozzle unit into an ultrasonic cleaning pool, then pouring cleaning liquid into the ultrasonic cleaning pool, standing and soaking for 8-15min, then starting ultrasonic cleaning equipment, carrying out comprehensive ultrasonic cleaning treatment on the base and the nozzle unit in the cleaning liquid for 20-30min, then taking out and washing, and drying by using drying equipment after washing, thereby completing the cleaning treatment of the welding part;

s3, assembling: firstly, one end of a nozzle unit to be welded is installed on an auxiliary installation fixing piece matched with the nozzle unit in position arrangement in a penetrating mode, pre-clamping is carried out through a clamping structure in each jack of the auxiliary installation fixing piece, then the auxiliary installation fixing piece is directly clamped through a clamp, the outer circle and the end face of a welding piece are aligned, and then the injector integral structural piece and the circular base are assembled and formed;

s4, welding: welding the integral structural part of the injector assembled in the step S3 with the circular base by welding equipment, sequentially welding the outermost circle and the innermost circle of the assembled nozzle units and the circular base, and finally, welding and fixing each nozzle unit one by one in a symmetrical mode to obtain the head injector;

s5, post-processing: and (5) washing the head injector welded in the step (S4) by using washing equipment, drying the head injector by using drying equipment, and sequentially carrying out a hydraulic test, an air tightness test and a leakage rate test on the dried head injector so as to complete the welding work of the whole head injector.

2. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: in the step S1, the circular base is formed by engraving a plurality of circles of nozzle unit groove groups from inside to outside by taking the circle center as a circular point, and each circle of nozzle unit groove group is composed of a plurality of uniformly distributed nozzle unit grooves.

3. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as defined in claim 2, wherein: every a plurality of through-hole has all been seted up in the nozzle unit inslot, and a plurality of through-hole is circular distribution in corresponding nozzle unit inslot.

4. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: and in the step S5, the leakage rate detection is to detect the whole injector through a helium mass spectrum leakage detection tool.

5. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: the cleaning liquid in the step S2 is one of sodium hydroxide lye, carbonic acid solution or glycerin organic solvent, and impurities and oil stains on the injector ring integral piece and the round base can be removed by the cleaning liquid.

6. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: the drying equipment in the steps S2 and S5 is a high-temperature vacuum drying and dehydrating all-in-one machine with the model of SUNDI-420W.

7. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: the auxiliary mounting fixture in step S3 includes a circular plate adapted to the circular base, the circular plate is provided with mounting holes adapted to the nozzle units, the positions of the mounting holes on the circular plate are arranged to correspond to the distribution of the nozzles on the circular base, and the inner side of the mounting holes is provided with a clamping portion adapted to the nozzle units.

8. The method for welding a multi-part structure of a liquid rocket engine thrust chamber head injector as recited in claim 1, wherein: the welding device in the step S4 is a vacuum electron beam welding machine.

Technical Field

The invention relates to the technical field of aerospace equipment processing, in particular to a multi-part structure welding method for a head injector of a thrust chamber of a liquid rocket engine.

Background

The liquid rocket engine is a liquid propellant rocket engine, namely a chemical rocket propulsion system using liquid chemical substances as energy sources and working media, common liquid oxidants comprise liquid oxygen, dinitrogen tetroxide and the like, combustion agents comprise liquid hydrogen, unsymmetrical dimethylhydrazine, kerosene and the like, the liquid oxidizer and the dinitrogen tetroxide are stored in different storage tanks, the liquid rocket engine generally comprises a thrust chamber, a propellant supply system and an engine control system, and the liquid rocket engine can be divided into an extrusion type and a pumping type according to the propellant supply system; the propellant components can be divided into single components, double components and three components; according to the function classification, the liquid rocket engine is used for space vehicles and ballistic missiles, and when the liquid rocket engine works, propellant and fuel are respectively extruded from a storage tank and enter a thrust chamber through a propellant conveying pipeline. The propellant is mixed and atomized by a nozzle at the head of the thrust chamber to form fine liquid drops, and the fine liquid drops are heated and gasified by flame in the combustion chamber and are violently combusted, so that the fine liquid drops become high-temperature high-pressure gas in the combustion chamber. The gas is accelerated into supersonic airflow through the nozzle and is ejected backwards, so that thrust acting on the engine is generated, the rocket is pushed to advance, and the thrust chamber is an important component for converting chemical energy of the liquid propellant into propulsive force. It is composed of propellant nozzle, combustion chamber and nozzle assembly. The propellant is injected into the combustion chamber through the injector, generates combustion products through the processes of atomization, evaporation, mixing, combustion and the like, and is flushed out of the spray pipe at high speed (2500-.

The welding of present liquid rocket engine thrust chamber head injector is comparatively loaded down with trivial details, and welding inefficiency, it is direct with a plurality ofly treat welded shower nozzle unit with one by one with the orifice on the PMKD assemble alignment and welding mostly, the operation is very complicated, can not realize will treating welded shower nozzle unit and carry out the welded position of whole assembly to the base earlier, carry out unified welding again and handle, can't reach not only quick but also convenient purpose of carrying out the welding, greatly increased producers' intensity of labour, production efficiency is reduced, thereby bring very big inconvenience for the production of room head injector.

Disclosure of Invention

Technical problem to be solved

Aiming at the defects of the prior art, the invention provides a multi-part structure welding method of a liquid rocket engine thrust chamber head injector, which solves the problems that the existing liquid rocket engine thrust chamber head injector is complicated in welding and low in welding efficiency, most of the existing liquid rocket engine thrust chamber head injectors are directly assembled, aligned and welded with spray holes in a fixed base plate one by one, the operation is very complicated, the spray head units to be welded cannot be integrally assembled to the welding position of a base firstly and then are uniformly welded, the purpose of quickly and conveniently welding cannot be achieved, the labor intensity of production personnel is greatly increased, and the production efficiency is reduced.

(II) technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme: the method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following steps:

s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through numerical control equipment, and then machining and manufacturing a welding part through machining equipment according to the process size requirement of the head injector required by the actual requirement;

s2, cleaning and impurity removing: washing the base and the nozzle unit which are subjected to the standard carving and machining in the step S1 for 2-3 times by using clean water, then putting the washed base and the washed nozzle unit into an ultrasonic cleaning pool, then pouring cleaning liquid into the ultrasonic cleaning pool, standing and soaking for 8-15min, then starting ultrasonic cleaning equipment, carrying out comprehensive ultrasonic cleaning treatment on the base and the nozzle unit in the cleaning liquid for 20-30min, then taking out and washing, and drying by using drying equipment after washing, thereby completing the cleaning treatment of the welding part;

s3, assembling: firstly, one end of a nozzle unit to be welded is installed on an auxiliary installation fixing piece matched with the nozzle unit in position arrangement in a penetrating mode, pre-clamping is carried out through a clamping structure in each jack of the auxiliary installation fixing piece, then the auxiliary installation fixing piece is directly clamped through a clamp, the outer circle and the end face of a welding piece are aligned, and then the injector integral structural piece and the circular base are assembled and formed;

s4, welding: welding the integral structural part of the injector assembled in the step S3 with the circular base by welding equipment, sequentially welding the outermost circle and the innermost circle of the assembled nozzle units and the circular base, and finally, welding and fixing each nozzle unit one by one in a symmetrical mode to obtain the head injector;

s5, post-processing: and (5) washing the head injector welded in the step (S4) by using washing equipment, drying the head injector by using drying equipment, and sequentially carrying out a hydraulic test, an air tightness test and a leakage rate test on the dried head injector so as to complete the welding work of the whole head injector.

Preferably, in the step S1, the circular base is formed by engraving a plurality of circles of nozzle unit groove groups from inside to outside with a circle center as a circular point, and each circle of nozzle unit groove group is formed by a plurality of uniformly distributed nozzle unit grooves.

Preferably, each nozzle unit groove is internally provided with a plurality of through holes which are circularly distributed in the corresponding nozzle unit groove.

Preferably, in the step S5, the leak rate detection is performed on the entire injector by using a helium mass spectrometer leak detection tool.

Preferably, the cleaning solution in step S2 is one of sodium hydroxide lye, carbonic acid solution or glycerin organic solvent, and impurities and oil stains on the injector ring integral piece and the circular base can be removed by the cleaning solution.

Preferably, the drying device in steps S2 and S5 is a high-temperature vacuum drying and dewatering all-in-one machine with model number SUNDI-420W.

Preferably, the auxiliary mounting fixture in step S3 includes a circular plate adapted to the circular base, the circular plate is provided with mounting holes adapted to the nozzle unit, the positions of the mounting holes on the circular plate are arranged to correspond to the distribution of the nozzles on the circular base, and the inner side of the mounting holes is provided with a clamping portion adapted to the nozzle unit.

Preferably, the welding device in step S4 is a vacuum electron beam welding machine.

(III) advantageous effects

The invention provides a method for welding a multi-part structure of a head injector of a thrust chamber of a liquid rocket engine. Compared with the prior art, the method has the following beneficial effects: the method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following steps: s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through numerical control equipment, and S2, cleaning and removing impurities: washing the base and the spray head unit which are subjected to the standard carving and machining in the step S1 for 2-3 times by using clean water, and then putting the base and the spray head unit which are subjected to the washing into an ultrasonic washing pool, S3, assembling: firstly, one end of a nozzle unit to be welded is penetratingly mounted on an auxiliary mounting fixing piece matched with the nozzle unit in position arrangement, and S4 and welding are carried out: welding the integral structural part of the injector assembled in the step S3 and the circular base by using a welding device, sequentially welding the outermost circle and the innermost circle of the assembled nozzle unit and the circular base, and S5, post-processing: the head injector welded in the step S4 is firstly washed by washing equipment, then is dried by drying equipment, and then is subjected to hydrostatic test, air tightness test detection and leakage rate detection in sequence, so that the welding work of the whole head injector is completed, the nozzle units to be welded can be integrally assembled to the welding position of the base firstly, and then is subjected to unified welding treatment, the purpose of rapid and convenient welding is well achieved, the welding is convenient, the welding efficiency is high, the nozzle units to be welded and the nozzle holes on the fixed bottom plate do not need to be assembled, aligned and welded one by one, the operation is simple, the labor intensity of production personnel is greatly reduced, and the production of the head injector is greatly facilitated.

Drawings

FIG. 1 is a flow chart of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1, the embodiment of the present invention provides three technical solutions: the method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following embodiments:

example 1

The method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following steps:

s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through a numerical control device, and processing and manufacturing a welding part through a machining device according to the process size requirement of the head injector required by actual needs, wherein the circular base is formed by engraving a plurality of circles of nozzle unit groove groups from inside to outside by taking a circle center as a circular point, each circle of nozzle unit groove group consists of a plurality of uniformly distributed nozzle unit grooves, each nozzle unit groove is internally provided with a plurality of through holes, and the plurality of through holes are circularly distributed in the corresponding nozzle unit grooves;

s2, cleaning and impurity removing: washing the base and the spray head unit which are subjected to the standard carving and machining in the step S1 for 2 times by using clean water, then putting the washed base and the washed spray head unit into an ultrasonic cleaning pool, then pouring cleaning liquid into the ultrasonic cleaning pool, standing and soaking for 12min, then starting ultrasonic cleaning equipment, carrying out comprehensive ultrasonic cleaning treatment on the base and the spray head unit in the cleaning liquid for 25min, then taking out the base and the spray head unit for washing, and drying the base and the spray head unit by using drying equipment after washing, thereby completing the cleaning treatment of a welding part, wherein the cleaning liquid is sodium hydroxide alkali liquor, and impurities and oil stains on the integral injector ring and the round base can be removed by using the cleaning liquid;

s3, assembling: one end of a nozzle unit to be welded is installed on an auxiliary installation fixing piece matched with the position arrangement of the nozzle unit in a penetrating mode, pre-clamping is carried out through a clamping structure inside each jack of the auxiliary installation fixing piece, then the auxiliary installation fixing piece is directly clamped through a clamp, the outer circle and the end face of a welding piece are aligned, then an integral structural piece of an injector and a circular base are assembled and formed, the auxiliary installation fixing piece comprises a circular plate matched with the circular base, installation holes matched with the nozzle unit are formed in the circular plate, the position arrangement of the installation holes in the circular plate corresponds to the spray hole distribution in the circular base, and a clamping portion matched with the nozzle unit is installed on the inner side of each installation hole;

s4, welding: welding the integral structural part of the injector assembled in the step S3 and the circular base through welding equipment, sequentially welding the outermost circle and the innermost circle welding seam positions of the spray head units and the circular base, and finally, welding and fixing each nozzle unit one by one in a symmetrical mode to obtain the head injector, wherein the welding equipment adopts a vacuum electron beam welding machine;

s5, post-processing: and (5) firstly washing the head injector welded in the step (S4) through washing equipment, then drying the head injector through drying equipment, and then sequentially carrying out hydraulic test, air tightness test detection and leakage rate detection on the dried head injector so as to complete the welding work of the whole head injector, wherein the leakage rate detection is to detect the whole head injector through a helium mass spectrum leakage detection tool.

In the embodiment of the invention, the drying equipment in the steps S2 and S5 is a high-temperature vacuum drying and dehydrating integrated machine with the model of SUNDI-420W.

Example 2

The method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following steps:

s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through a numerical control device, and processing and manufacturing a welding part through a machining device according to the process size requirement of the head injector required by actual needs, wherein the circular base is formed by engraving a plurality of circles of nozzle unit groove groups from inside to outside by taking a circle center as a circular point, each circle of nozzle unit groove group consists of a plurality of uniformly distributed nozzle unit grooves, each nozzle unit groove is internally provided with a plurality of through holes, and the plurality of through holes are circularly distributed in the corresponding nozzle unit grooves;

s2, cleaning and impurity removing: washing the base and the spray head unit which are subjected to the standard carving and machining in the step S1 for 3 times by using clean water, then putting the washed base and the washed spray head unit into an ultrasonic cleaning pool, then pouring cleaning liquid into the ultrasonic cleaning pool, standing and soaking for 8min, starting ultrasonic cleaning equipment, carrying out comprehensive ultrasonic cleaning treatment on the base and the spray head unit in the cleaning liquid for 20min, then taking out the base and the spray head unit for washing, and drying the base and the spray head unit by using drying equipment after washing, thereby completing the cleaning treatment of a welding part, wherein the cleaning liquid is carbonic acid solution, and impurities and oil stains on the integral injector ring and the round base can be removed by using the cleaning liquid;

s3, assembling: one end of a nozzle unit to be welded is installed on an auxiliary installation fixing piece matched with the position arrangement of the nozzle unit in a penetrating mode, pre-clamping is carried out through a clamping structure inside each jack of the auxiliary installation fixing piece, then the auxiliary installation fixing piece is directly clamped through a clamp, the outer circle and the end face of a welding piece are aligned, then an integral structural piece of an injector and a circular base are assembled and formed, the auxiliary installation fixing piece comprises a circular plate matched with the circular base, installation holes matched with the nozzle unit are formed in the circular plate, the position arrangement of the installation holes in the circular plate corresponds to the spray hole distribution in the circular base, and a clamping portion matched with the nozzle unit is installed on the inner side of each installation hole;

s4, welding: welding the integral structural part of the injector assembled in the step S3 and the circular base through welding equipment, sequentially welding the outermost circle and the innermost circle welding seam positions of the spray head units and the circular base, and finally, welding and fixing each nozzle unit one by one in a symmetrical mode to obtain the head injector, wherein the welding equipment adopts a vacuum electron beam welding machine;

s5, post-processing: and (5) firstly washing the head injector welded in the step (S4) through washing equipment, then drying the head injector through drying equipment, and then sequentially carrying out hydraulic test, air tightness test detection and leakage rate detection on the dried head injector so as to complete the welding work of the whole head injector, wherein the leakage rate detection is to detect the whole head injector through a helium mass spectrum leakage detection tool.

In the embodiment of the invention, the drying equipment in the steps S2 and S5 is a high-temperature vacuum drying and dehydrating integrated machine with the model of SUNDI-420W.

Example 3

The method for welding the multi-part structure of the injector at the head of the thrust chamber of the liquid rocket engine specifically comprises the following steps:

s1, pre-welding treatment: firstly, marking a plurality of cross welding references on the lower end face of a circular base of a head injector of a thrust chamber of a liquid rocket engine through a numerical control device, and processing and manufacturing a welding part through a machining device according to the process size requirement of the head injector required by actual needs, wherein the circular base is formed by engraving a plurality of circles of nozzle unit groove groups from inside to outside by taking a circle center as a circular point, each circle of nozzle unit groove group consists of a plurality of uniformly distributed nozzle unit grooves, each nozzle unit groove is internally provided with a plurality of through holes, and the plurality of through holes are circularly distributed in the corresponding nozzle unit grooves;

s2, cleaning and impurity removing: washing the base and the spray head unit which are subjected to the standard carving and machining in the step S1 for 2 times by using clean water, then putting the washed base and the washed spray head unit into an ultrasonic cleaning pool, then pouring cleaning liquid into the ultrasonic cleaning pool, standing and soaking for 15min, then starting ultrasonic cleaning equipment, carrying out comprehensive ultrasonic cleaning treatment on the base and the spray head unit in the cleaning liquid for 30min, then taking out the base and the spray head unit for washing, and drying the base and the spray head unit by using drying equipment after washing, thereby completing the cleaning treatment of a welding part, wherein the cleaning liquid is a glycerol organic solvent, and impurities and oil stains on the integral injector ring and the round base can be removed by using the cleaning liquid;

s3, assembling: one end of a nozzle unit to be welded is installed on an auxiliary installation fixing piece matched with the position arrangement of the nozzle unit in a penetrating mode, pre-clamping is carried out through a clamping structure inside each jack of the auxiliary installation fixing piece, then the auxiliary installation fixing piece is directly clamped through a clamp, the outer circle and the end face of a welding piece are aligned, then an integral structural piece of an injector and a circular base are assembled and formed, the auxiliary installation fixing piece comprises a circular plate matched with the circular base, installation holes matched with the nozzle unit are formed in the circular plate, the position arrangement of the installation holes in the circular plate corresponds to the spray hole distribution in the circular base, and a clamping portion matched with the nozzle unit is installed on the inner side of each installation hole;

s4, welding: welding the integral structural part of the injector assembled in the step S3 and the circular base through welding equipment, sequentially welding the outermost circle and the innermost circle welding seam positions of the spray head units and the circular base, and finally, welding and fixing each nozzle unit one by one in a symmetrical mode to obtain the head injector, wherein the welding equipment adopts a vacuum electron beam welding machine;

s5, post-processing: and (5) firstly washing the head injector welded in the step (S4) through washing equipment, then drying the head injector through drying equipment, and then sequentially carrying out hydraulic test, air tightness test detection and leakage rate detection on the dried head injector so as to complete the welding work of the whole head injector, wherein the leakage rate detection is to detect the whole head injector through a helium mass spectrum leakage detection tool.

In the embodiment of the invention, the drying equipment in the steps S2 and S5 is a high-temperature vacuum drying and dehydrating integrated machine with the model of SUNDI-420W.

In conclusion, the invention can realize that the nozzle units to be welded are integrally assembled to the welding position of the base and then are uniformly welded, thereby well achieving the purpose of quickly and conveniently welding, having convenient welding and high welding efficiency, having no need of assembling, aligning and welding a plurality of nozzle units to be welded with the spray holes on the fixed bottom plate one by one, having simple operation, greatly reducing the labor intensity of production personnel, and greatly facilitating the production of the injector at the head part of the chamber.

And those not described in detail in this specification are well within the skill of those in the art.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.