CN111751100A - Engine nozzle machining, installing and debugging method - Google Patents
Engine nozzle machining, installing and debugging method Download PDFInfo
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- CN111751100A CN111751100A CN202010615121.2A CN202010615121A CN111751100A CN 111751100 A CN111751100 A CN 111751100A CN 202010615121 A CN202010615121 A CN 202010615121A CN 111751100 A CN111751100 A CN 111751100A
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- 238000000034 method Methods 0.000 title claims abstract description 36
- 238000003754 machining Methods 0.000 title claims description 20
- 238000012360 testing method Methods 0.000 claims abstract description 36
- 238000013461 design Methods 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 5
- 238000012795 verification Methods 0.000 claims description 4
- 230000013011 mating Effects 0.000 claims 2
- 238000012545 processing Methods 0.000 abstract description 16
- 238000012797 qualification Methods 0.000 abstract description 6
- 238000011056 performance test Methods 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000013101 initial test Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M10/00—Hydrodynamic testing; Arrangements in or on ship-testing tanks or water tunnels
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- General Physics & Mathematics (AREA)
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- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a method for processing, installing and debugging an engine nozzle, which comprises the steps of obtaining key accessory parts influencing the performance of the nozzle, adopting an orthogonal test to the selected key characteristic parts according to the key characteristic parts of the key accessory parts to obtain the key characteristic dimension of the key accessory parts, obtaining the key characteristic dimension corresponding to the best nozzle performance by using a key characteristic dimension and performance matching relation test of the key accessory parts, solidifying the key characteristic dimension tolerance and the cutting parameters of the key accessory parts according to the corresponding relation of the key characteristic dimension and the performance, not reserving the dimension allowance of the key characteristic parts, ensuring the processing and assembling precision of the parts, changing the current situation that the performance of the nozzle is unstable due to the fact that the nozzle is manually involved in the process of debugging the performance of the nozzle, reducing the labor intensity and the working difficulty of operators, and improving the performance stability of the nozzle after debugging, the debugging qualification rate of the nozzle is improved by more than 1.5 times, and the debugging efficiency is improved by more than 3 times.
Description
Technical Field
The invention belongs to the field of nozzle performance debugging, and particularly relates to a method for processing, installing and debugging an engine nozzle.
Background
The engine nozzle is generally formed by assembling dozens of parts, according to different functions, the performance requirements such as certain flow, angle and atomization need to be met after the engine nozzle is assembled, the performance requirements are influenced by the surface quality, the size and the performance consistency of matched components, and the flow, the angle and the atomization performance of the assembled nozzle need to meet the design requirements through performance debugging. The traditional performance debugging method mainly comprises the steps of initially testing the performance by using special performance testing equipment after a nozzle is assembled, and then repeatedly repairing and researching the part influencing the performance according to the testing result and the working experience of an operator. The performance deviation design requirement of different nozzles in the same batch after initial test is larger and the discreteness is larger, the process of performance test → disqualification → repair and research → performance test → disqualification → regress is repeated for a plurality of times during debugging, the performance requirement of the design performance can be ensured, the first performance test qualification rate is less than 10%, the whole debugging difficulty is large, the qualification rate is low, the period is long, and the requirement on the skill level of an operator is extremely high. In addition, after key characteristic parts of the nozzle matching parts are manually repaired and researched for multiple times, the deviation between the characteristic size and the appearance and the theoretical appearance is large, the discreteness of batch parts is large, the performance of the finally debugged qualified fuel nozzle is unstable, and the performance attenuation can occur after the nozzle matching parts are used for a period of time, so that the safety and the reliability of an engine are seriously influenced.
Disclosure of Invention
The invention aims to provide a method for machining, installing and debugging an engine nozzle, which overcomes the defects of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method for processing, installing and debugging an engine nozzle comprises the following steps:
step 1), acquiring key matched parts influencing the performance of the nozzle according to the performance requirement of the nozzle and the theoretical basis of fluid mechanics;
step 2), obtaining key characteristic parts of the key accessory according to the structure of the key accessory, and obtaining the key characteristic size of the key accessory by adopting an orthogonal test on the selected key characteristic parts;
step 3), in the single piece machining process of the key accessory, performing a key characteristic dimension and performance matching relation test on the key accessory to obtain a key characteristic dimension corresponding to the optimal nozzle performance;
and 4) solidifying the tolerance of the critical characteristic dimension and the cutting parameters of the critical characteristic part to process the critical accessory part according to the corresponding relation between the critical characteristic dimension and the performance, and assembling the processed accessory part to carry out trace repairing and grinding to finish the performance debugging of the engine nozzle.
Furthermore, the matched part corresponding to the parameter value which has the largest influence on the working state of the nozzle is a key matched part.
Further, the key characteristic part is a part influencing parameter values of the key accessory.
Furthermore, the corresponding nozzle performance indexes when the key characteristic dimension is different values are tested.
Further, according to the test result, a corresponding relation between the critical characteristic dimension and the performance is established, and the critical characteristic dimension corresponding to the optimal nozzle performance is obtained.
Further, when the matching relation test is carried out, the Bernoulli equation is adopted to theoretically calculate the key characteristic dimension and performance.
Further, the final performance requirement tolerance of the nozzle is 50% to 80% of the design tolerance.
Furthermore, when the matching relation test is carried out, other parts except the key matching parts are all qualified standard parts.
Further, the repairing amount of the repairing and grinding is not more than 0.01 mm.
Further, the key matching parts obtained by processing the solidified key characteristic dimension tolerance and the cutting parameters of the key characteristic parts are subjected to component debugging and verification, and the key characteristic parts meeting the processing dimension requirements are obtained and assembled.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention relates to a method for processing, installing and debugging an engine nozzle, which is characterized in that a key accessory influencing the performance of the nozzle is obtained according to the performance requirement of the nozzle and the theoretical basis of fluid mechanics, a key characteristic part of the key accessory is obtained according to the structure of the key accessory, and an orthogonal test is carried out on the selected key characteristic part to obtain the key characteristic dimension of the key accessory; the method comprises the steps of carrying out a key characteristic dimension and performance matching relation test on key matching parts in the key matching part single-piece processing process to obtain a key characteristic dimension corresponding to the best nozzle performance, solidifying key characteristic dimension tolerance and cutting parameters of the key characteristic parts according to the corresponding relation between the key characteristic dimension and the performance to process the key matching parts, not reserving the dimension allowance of key characteristic parts, ensuring the processing and assembling precision of parts, changing the current situation that the nozzle performance is unstable due to manual participation in the nozzle performance debugging process, reducing the labor intensity and the working difficulty of operators, improving the performance stability of the nozzle after debugging, improving the nozzle debugging qualification rate by more than 1.5 times, and improving the debugging efficiency by more than 3 times.
Drawings
FIG. 1 is a schematic view of an engine nozzle according to an embodiment of the present invention.
FIG. 2 is a schematic view of a structure of a swirling core in an embodiment of the present invention.
Fig. 3 is a cross-sectional view of fig. 2B-B.
Wherein, 1, swirl core.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
a method for processing, installing and debugging an engine nozzle comprises the following steps:
step 1), acquiring key matched parts influencing the performance of the nozzle according to the performance requirement of the nozzle and the theoretical basis of fluid mechanics;
acquiring key accessory parts influencing the performance of the nozzle, namely acquiring the influence parameters of the working state of the nozzle based on the performance requirements of the nozzle and the theoretical basis of hydromechanics, wherein the accessory parts which most correspond to the influence parameters are the key accessory parts;
step 2), obtaining key characteristic parts of the key accessory according to the structure of the key accessory, and obtaining the key characteristic size of the key accessory by adopting an orthogonal test on the selected key characteristic parts;
the key characteristic part is a part influencing the parameter value of the key accessory.
Step 3), in the single piece machining process of the key matching parts, carrying out a key characteristic dimension and performance matching relation test on the key matching parts, and establishing a corresponding relation between the key characteristic dimension and the performance according to the test result to obtain the key characteristic dimension corresponding to the optimal nozzle performance;
specifically, testing the corresponding nozzle performance indexes when the key characteristic sizes are different values; if the key characteristic dimension is M, when key matching parts are machined, sequentially machining 3-10 groups of M with different thicknesses according to M, M-delta M, M-2 delta M and M-3 delta M … …, wherein M is the dimension required by a design drawing, delta M is a tolerance, and the value is generally set to be 0.005mm-0.05mm according to the requirement of flow tolerance delta M; and establishing a corresponding relation between the key characteristic dimension and the performance according to the test result to obtain the key characteristic dimension corresponding to the optimal nozzle performance.
When a matching relation test is carried out, theoretical calculation is carried out on key characteristic size and performance by adopting a Bernoulli equation; all the parts except the key matching parts are qualified standard parts; the final performance of the nozzle requires a tolerance of 50% to 80% of the design tolerance in order to eliminate the impact of other non-critical kit parts on the final performance of the nozzle.
And 4) solidifying the tolerance of the critical characteristic dimension and the cutting parameters of the critical characteristic part to process the critical accessory part according to the corresponding relation between the critical characteristic dimension and the performance, assembling the processed accessory part, testing, repairing and grinding, and finishing the micro-debugging of the engine nozzle. The repairing amount of the repairing and grinding is not more than 0.01 mm. In the step 4), the key accessory parts obtained by processing the solidified key characteristic dimension tolerance and the cutting parameters of the key characteristic parts are subjected to component debugging and verification, the key characteristic parts meeting the processing dimension requirements are obtained and assembled, and the problem that the processing dimension of the key accessory parts is inaccurate due to processing errors, so that the processed accessory parts are assembled and tested unqualifiedly is avoided.
Example (b):
according to the method, the fine adjustment verification is carried out on the auxiliary oil way of the nozzle according to the performance requirement of the nozzle and the theoretical basis of fluid mechanics, as shown in figures 1-3:
1. according to the performance requirements of the nozzle and the related theoretical basis of hydromechanics, finding out a key matched part influencing the flow performance of the secondary oil path of the nozzle as a swirl core 1, wherein the key characteristic part of the swirl core 1 is a swirl groove K;
2. according to the swirl groove K at the found key characteristic part, finding out the key characteristic dimension of the key matched part as the groove depth H of the swirl groove by adopting an orthogonal test;
3. when the swirl core 1 is processed, a swirl groove depth H and auxiliary oil way flow performance matching relation test is carried out, namely, the swirl groove depths are processed in groups according to H, H-0.01mm, H-0.02mm and … H-0.05 mm; respectively loading the swirl cores 1 of different groups into the fuel nozzle, testing the flow performance value of the auxiliary oil way, and establishing the corresponding relation between the groove depth H of the swirl core and the flow performance of the auxiliary oil way of the nozzle; and finally, starting to process the batch rotational flow core parts according to the determined optimal rotational flow groove depth value.
4. And (3) according to the optimal depth value of the swirl groove, solidifying the dimensional tolerance of the depth H of the swirl groove and the cutting parameters for machining the swirl groove in the process procedure to machine the swirl core 1, and after machining, installing the auxiliary oil way of the nozzle and testing the performance of the nozzle.
Setting a repeated test frequency of 50, processing 50 cyclone cores 1, performing a repeated test on the 50 th cyclone core after the repeated test frequency is reached, and if the repeated test is qualified, continuously processing subsequent parts; if the test result is not qualified, the 49 th piece is tested, and if the test result is not qualified, the 48 th piece is tested, and all the cyclone cores 1 are detected. And parts which are unqualified to be tested are stored in an isolated mode, and parts which have smaller deviation test requirements can be saved in the subsequent component debugging process by adopting a traditional debugging mode. And (3) completing the assembly of the nozzle assembly on the rotational flow core 1 which is qualified through inspection, testing the performance of the nozzle, directly packaging and warehousing the rotational flow core if the performance is qualified, and slightly repairing and grinding the key characteristic size according to the matching relation between the key characteristic size and the performance established in the early stage if the performance is unqualified so as to meet the performance requirement. In the experimental process, the nozzle performance test is carried out, the product percent of pass reaches more than 90%, the rest is required to be repaired and ground, the repairing and grinding amount of the repairing and grinding is not more than 0.01mm, and the micro-debugging of the engine nozzle can be completed. The method is simple and high in qualification rate, changes the current situation that the performance of the nozzle is unstable due to manual participation in the process of debugging the performance of the nozzle, reduces the labor intensity and the working difficulty of operators, improves the performance stability of the nozzle after debugging, improves the debugging qualification rate of the nozzle by more than 1.5 times, and improves the debugging efficiency by more than 3 times.
Claims (10)
1. The method for machining, installing and debugging the engine nozzle is characterized by comprising the following steps of:
step 1), acquiring key matched parts influencing the performance of the nozzle according to the performance requirement of the nozzle and the theoretical basis of fluid mechanics;
step 2), obtaining key characteristic parts of the key accessory according to the structure of the key accessory, and obtaining the key characteristic size of the key accessory by adopting an orthogonal test on the selected key characteristic parts;
step 3), in the single piece machining process of the key accessory, performing a key characteristic dimension and performance matching relation test on the key accessory to obtain a key characteristic dimension corresponding to the optimal nozzle performance;
and 4) solidifying the tolerance of the critical characteristic dimension and the cutting parameters of the critical characteristic part to process the critical accessory part according to the corresponding relation between the critical characteristic dimension and the performance, and assembling the processed accessory part to carry out trace repairing and grinding to finish the performance debugging of the engine nozzle.
2. The method for machining, installing and debugging the nozzle of the engine as claimed in claim 1, wherein the mating part corresponding to the parameter value having the greatest influence on the working state of the nozzle is a key mating part.
3. The method for machining, installing and debugging the engine nozzle as claimed in claim 1, wherein the critical characteristic part is a part affecting a parameter value of a critical kit part.
4. The method for machining, installing and debugging the engine nozzle as claimed in claim 1, wherein the corresponding nozzle performance index is tested when the critical characteristic dimension is different values.
5. The method as claimed in claim 1, wherein the correspondence between critical feature size and performance is established according to the test results to obtain the critical feature size corresponding to the best nozzle performance.
6. The method for machining, installing and debugging an engine nozzle according to claim 4, wherein when the matching relation test is performed, the Bernoulli equation is used for theoretically calculating the key characteristic dimension and the performance.
7. The method for machining, installing and debugging the nozzle of the engine as claimed in claim 4, wherein the final performance requirement tolerance of the nozzle is 50-80% of the design tolerance.
8. The method for machining, installing and debugging the engine nozzle as claimed in claim 4, wherein when the matching relationship test is performed, all parts except the key matching parts are qualified standard parts.
9. The method for machining, installing and debugging an engine nozzle according to claim 1, wherein the amount of lapping is not more than 0.01 mm.
10. The engine nozzle machining, mounting and debugging method of claim 1, wherein the key kit parts obtained by machining the solidified critical characteristic dimensional tolerance and the cutting parameters of the critical characteristic parts are subjected to component debugging and verification, and the critical characteristic parts meeting the machining dimensional requirements are obtained and assembled.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010615121.2A CN111751100A (en) | 2020-06-30 | 2020-06-30 | Engine nozzle machining, installing and debugging method |
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| CN202010615121.2A CN111751100A (en) | 2020-06-30 | 2020-06-30 | Engine nozzle machining, installing and debugging method |
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| CN111751100A true CN111751100A (en) | 2020-10-09 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2008128585A (en) * | 2008-07-15 | 2010-01-20 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" (RU) | METHOD FOR DEBUGGING A GAS TURBINE ENGINE WITH AN AFTER CHAMBER |
| CN105631110A (en) * | 2015-12-25 | 2016-06-01 | 潍柴动力扬州柴油机有限责任公司 | Design method of key structural parameters of piston cooling nozzle |
| CN107763654A (en) * | 2017-09-28 | 2018-03-06 | 中国航发动力股份有限公司 | A kind of flow adjustment method of compact-type built-in fuel injection ring |
| CN111055051A (en) * | 2019-12-27 | 2020-04-24 | 成立航空技术有限公司 | Device and method for debugging flow of multi-nozzle welding assembly |
-
2020
- 2020-06-30 CN CN202010615121.2A patent/CN111751100A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2008128585A (en) * | 2008-07-15 | 2010-01-20 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" (RU) | METHOD FOR DEBUGGING A GAS TURBINE ENGINE WITH AN AFTER CHAMBER |
| CN105631110A (en) * | 2015-12-25 | 2016-06-01 | 潍柴动力扬州柴油机有限责任公司 | Design method of key structural parameters of piston cooling nozzle |
| CN107763654A (en) * | 2017-09-28 | 2018-03-06 | 中国航发动力股份有限公司 | A kind of flow adjustment method of compact-type built-in fuel injection ring |
| CN111055051A (en) * | 2019-12-27 | 2020-04-24 | 成立航空技术有限公司 | Device and method for debugging flow of multi-nozzle welding assembly |
Non-Patent Citations (2)
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| 熊成红 等: "双油路离心喷嘴流量与喷雾锥角相关性研究", 《探索创新交流(第二集)第二届中国航空学会青年科技论坛文集》 * |
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Application publication date: 20201009 |