CN117644478A - Performance improvement method for aircraft multi-stage supercharged jet engine - Google Patents
Performance improvement method for aircraft multi-stage supercharged jet engine Download PDFInfo
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- CN117644478A CN117644478A CN202410121479.8A CN202410121479A CN117644478A CN 117644478 A CN117644478 A CN 117644478A CN 202410121479 A CN202410121479 A CN 202410121479A CN 117644478 A CN117644478 A CN 117644478A
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- 238000000034 method Methods 0.000 title claims abstract description 22
- 229910003460 diamond Inorganic materials 0.000 claims abstract description 36
- 239000010432 diamond Substances 0.000 claims abstract description 36
- 239000000843 powder Substances 0.000 claims abstract description 33
- 239000002245 particle Substances 0.000 claims abstract description 20
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 12
- 239000000956 alloy Substances 0.000 claims abstract description 12
- 238000005299 abrasion Methods 0.000 claims abstract description 4
- 230000001105 regulatory effect Effects 0.000 claims abstract description 4
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical group O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 10
- 229910000601 superalloy Inorganic materials 0.000 claims description 3
- 239000012530 fluid Substances 0.000 abstract description 6
- 238000007789 sealing Methods 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 10
- 239000000203 mixture Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 239000012535 impurity Substances 0.000 description 4
- 238000005498 polishing Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000010419 fine particle Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The invention discloses a performance improving method of an aircraft multi-stage booster jet engine, which relates to the technical field of engine performance improvement, wherein when the multi-stage booster jet engine is tested, the power of the multi-stage booster jet engine is adjusted to a first power for operation, and diamond grits with larger particle sizes are continuously filled at the front end of the multi-stage booster jet engine; adjusting the power of the multi-stage booster jet engine to a second power for operation, wherein the second power is higher than the first power, and continuously filling diamond grits with smaller particle sizes at the front end of the second power; the power of the multi-stage supercharged jet engine is adjusted to be operated at a third power, the third power is higher than the second power, and the front end of the multi-stage supercharged jet engine is not added at all; regulating the power of the multi-stage supercharged jet engine to a second power operation, and continuously filling high-temperature alloy powder into the front end of the multi-stage supercharged jet engine; the multi-stage supercharged jet engine is kept to operate at the second power, and high-temperature and abrasion-resistant powder is continuously filled at the front end of the multi-stage supercharged jet engine. The invention can reduce the fluid resistance of the engine, further reduce the working temperature of the engine, and simultaneously ensure that the sealing compact thrust is larger.
Description
Technical Field
The invention relates to the technical field of engine performance improvement, in particular to a performance improvement method of an aircraft multi-stage supercharged jet engine.
Background
The thrust of the aircraft engine is better than the performance of the aircraft engine which is directly affected. The working principle for jet engines is: the fuel and gas mixture enters the engine combustion chamber, and the fuel is hydraulically injected by an injector and mixed with air to form a combustion mixture. The compressor then compresses the air to a high pressure to highly excite the combustion mixture, and when an ignition spark ignites the mixture, the combustion mixture burns rapidly, hot gases are exhausted, the hot gases propel the impeller, the motion of the impeller is converted into mechanical energy, and the mechanical energy drives the aircraft forward. In addition, the engine is also provided with a turbocharging device which can effectively increase the compression ratio of the engine, improve the performance of the engine and increase the thrust. When the engine works, hot gas passes through the turbocharger from the combustion chamber, the turbine rotates under the action of the hot gas, the compression degree of the hot gas is further improved, and then the hot gas enters the combustion chamber, so that the combustion effect of the combustion mixture is enhanced, and the thrust of the engine is improved.
The jet engine operation includes:
1. inspiration: the air enters an engine room and is compressed to a certain pressure and temperature by an impeller;
2. spraying: fuel and air are injected into the engine compartment and combusted in the combustion chamber;
3. pushing: the burnt gas pushes the impeller to move outwards to generate energy;
4. and (3) exhausting: the exhausted hot gas and exhaust gas pass through the exhaust nozzle and are exhausted from the engine room under static pressure;
5. and (3) cooling: the temperature of the engine room is reduced by the cooling system, enabling the engine to continue to operate.
Because the whole working flow of the multi-stage supercharged jet engine is a fluid flow working process, the invention is based on a scheme capable of improving the power of the engine: and performing a plurality of flow processes on the assembled multi-stage supercharged jet engine to improve the engine performance.
Disclosure of Invention
The invention aims to provide a performance improving method of an aircraft multi-stage supercharged jet engine, which aims to solve the problems in the prior art, reduce the fluid resistance of the engine, further reduce the working temperature of the engine and simultaneously ensure that the sealing compact thrust is larger.
In order to achieve the above object, the present invention provides the following solutions:
the invention provides a performance improving method of an aircraft multi-stage supercharged jet engine, which comprises the following steps:
s1, when the assembled multi-stage booster jet engine is tested, adjusting the power of the multi-stage booster jet engine to a first power for operation, and continuously filling diamond gravel at the front end of the multi-stage booster jet engine;
s2, stopping filling the diamond grit, regulating the power of the multi-stage booster jet engine to a second power, wherein the second power is higher than the first power, continuously filling the diamond grit at the front end of the multi-stage booster jet engine, and the grain size of the diamond grit in S2 is smaller than that of the diamond grit in S1;
s3, stopping filling diamond gravel, and adjusting the power of the multi-stage booster jet engine to be operated at a third power, wherein the third power is higher than the second power, and the front end of the multi-stage booster jet engine is not added at all;
s4, adjusting the power of the multi-stage booster jet engine to a second power operation, and continuously filling high-temperature alloy powder into the front end of the multi-stage booster jet engine;
s5, stopping filling the high-temperature alloy powder, keeping the multi-stage supercharged jet engine to run at the second power, and continuously filling the high-temperature resistant and wear-resistant powder at the front end of the multi-stage supercharged jet engine.
Preferably, the first power is 75%, the second power is 85%, and the third power is 95%.
Preferably, in S1, the diamond grit has a particle size of 50 microns and is continuously charged for 80 minutes at 0.4 kg/min.
Preferably, in S2, the diamond grit has a particle size of 20 microns and is added for 80 minutes at 0.25 kg/min.
Preferably, in S4, the superalloy powder has a particle size of 5 microns and is added at 0.15 kg/min for 80 minutes.
Preferably, in S5, the high temperature resistant and abrasion resistant powder is zirconia powder.
Preferably, in S5, the particle size of the high temperature resistant and abrasion resistant powder is 1-2 microns, and 0.1 kg/min is continuously filled for 150 minutes.
Compared with the prior art, the invention has the following technical effects:
according to the performance improvement method of the aircraft multi-stage booster jet engine, when the assembled multi-stage booster jet engine is tested, the power of the multi-stage booster jet engine is respectively adjusted to be operated with two different powers, and two diamond grits with different particle sizes are respectively and continuously filled at the front end of the multi-stage booster jet engine, so that the protrusions on the inner wall of the whole cavity of the tail nozzle from the air inlet of the multi-stage booster jet engine are polished through the diamond grits, impurities and rough surfaces are removed, the fluid resistance and fit clearance are reduced, and the diamond grits with large particle sizes are polished firstly and then the diamond grits with small particle sizes are polished, so that the polishing effect and polishing efficiency can be improved; after the diamond gravel is stopped being filled, the power of the multi-stage booster jet engine is adjusted to be in third power operation, the third power is higher than the second power, the front end of the multi-stage booster jet engine is not added, the multi-stage booster jet engine is operated with larger power, impurities left in the steps can be brought to the tail nozzle to be discharged, and the whole cavity is cleaned; the power of the multi-stage booster jet engine is adjusted to the second power for operation, high-temperature alloy powder is continuously filled at the front end of the multi-stage booster jet engine, pits on the inner wall of the whole cavity are filled by the high-temperature alloy powder, effective gaps are reduced, namely, redundant space in the cavity is reduced, vortex generation is effectively avoided, the thrust force of the multi-stage booster jet engine of an airplane is larger, and under the condition of the same oil quantity, the thrust force of the multi-stage booster jet engine of the airplane processed by the performance improvement method can be improved by 23 percent, and the temperature of tail jet flow can be reduced by 357 ℃ through experiments; after the high-temperature alloy powder is stopped being filled, the multistage supercharged jet engine is kept to run at the second power, the front end of the multistage supercharged jet engine is continuously filled with the high-temperature and wear-resistant powder, the inner wall of the cavity is filled and coated again by using the high-temperature and wear-resistant powder, the overall hardness and high-temperature resistance are effectively improved, and the overall service life is prolonged to a certain extent.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of the structure of an aircraft multi-stage supercharged jet engine according to the present invention;
FIG. 2 is a schematic view of the internal structure of an aircraft multi-stage supercharged jet engine according to the present invention;
in the figure: 1-air inlet, 2-compressor, 3-combustion chamber, 4-turbine, 5-tail nozzle.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a performance improving method of an aircraft multi-stage supercharged jet engine, which aims to solve the technical problems of high fluid resistance, high working temperature and small thrust of the existing aircraft engine.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1-2, the present embodiment provides a performance enhancing method of an aircraft multi-stage booster jet engine, including the following steps:
s1, when the assembled multi-stage booster jet engine is tested, adjusting the power of the multi-stage booster jet engine to a first power for operation, and continuously filling diamond gravel at the front end of the multi-stage booster jet engine;
s2, stopping filling the diamond grit, regulating the power of the multi-stage booster jet engine to a second power, wherein the second power is higher than the first power, continuously filling the diamond grit at the front end of the multi-stage booster jet engine, and the grain size of the diamond grit in S2 is smaller than that of the diamond grit in S1;
the power of the multi-stage booster jet engine is respectively adjusted to be operated with two different powers, diamond grits with two different particle sizes are respectively and continuously filled at the front end of the multi-stage booster jet engine, so that protrusions on the inner wall of the whole cavity of the multi-stage booster jet engine from the air inlet 1 to the tail nozzle 5 are polished through the diamond grits, impurities and rough surfaces are removed, the fluid resistance and fit clearance are reduced, and the diamond grits with large particle sizes are polished firstly, and then the diamond grits with small particle sizes are polished, so that the polishing effect and polishing efficiency can be improved;
s3, stopping filling diamond gravel, adjusting the power of the multi-stage booster jet engine to be higher than the second power, and operating the multi-stage booster jet engine at a higher power without any addition at the front end of the multi-stage booster jet engine, so that impurities left in the steps above can be brought to the tail nozzle 5 to be discharged, and cleaning the whole cavity is realized;
s4, adjusting the power of the multistage booster jet engine to a second power for operation, and continuously filling high-temperature alloy powder into the front end of the multistage booster jet engine, wherein all the surfaces of smooth parts are provided with concave-convex textures at a microscopic angle, so that pits on the inner wall of the whole cavity are filled with the high-temperature alloy powder, effective gaps are reduced, namely, the redundant space in the cavity is reduced, vortex generation is effectively avoided, the thrust force of the aircraft multistage booster jet engine is larger, and the thrust force of the aircraft multistage booster jet engine processed by the performance improvement method can be improved by 23% under the condition of the same oil quantity through experiments, and the temperature of tail jet flow can be reduced by 357 ℃;
s5, stopping filling high-temperature alloy powder, keeping the multi-stage supercharged jet engine to run at the second power, continuously filling high-temperature-resistant and wear-resistant powder at the front end of the multi-stage supercharged jet engine, and enabling fine particles to be impacted in microscopic pits at high speed by high-speed airflow to form deposition and fix, so that the inner wall of the cavity is filled and coated again by the high-temperature-resistant and wear-resistant powder, the overall hardness and high-temperature resistance are effectively improved, and the overall service life is prolonged to a certain extent.
Specifically, the first power is 75%, the second power is 85%, and the third power is 95%.
In S1, the diamond grit particle size was 50 microns and 0.4 kg/min was continuously charged for 80 minutes.
In S2, the diamond grit particle size was 20 microns, and 0.25 kg/min was continuously charged for 80 minutes.
In S4, the superalloy powder had a particle size of 5 microns and was added at 0.15 kg/min for 80 minutes.
In S5, the high-temperature-resistant and wear-resistant powder is zirconia powder, preferably high-purity zirconia powder, has high hardness, can realize wear resistance, and has high-temperature resistance.
In S5, the particle size of the high-temperature-resistant and wear-resistant powder is 1-2 microns, and 0.1 kg/min is continuously filled for 150 minutes.
However, the parameters in the present embodiment are not limited to the above-mentioned limitations, and those skilled in the art can adapt them according to actual needs.
The flow paths of the diamond grits, the high-temperature alloy powder and the high-purity zirconia powder are the whole inner wall from the air inlet 1 to the direction of the tail nozzle 5, and sequentially pass through the corresponding inner wall at the air inlet 1, the corresponding inner wall at the compressor 2, the corresponding inner wall at the combustion chamber 3, the corresponding inner wall at the turbine 4 and the corresponding inner wall at the tail nozzle 5.
Through the technological design of this implementation, act on the whole inner wall of aircraft multistage booster jet engine to polish, fill, clean and form high temperature resistant wearing layer to its inner wall, make the effective clearance of the inner wall surface of aircraft multistage booster jet engine reduce, holistic high temperature resistance and wearing performance improve, make self windage reduce simultaneously, the fit clearance is littleer, therefore make the thrust ratio of aircraft multistage booster jet engine bigger, the bulk temperature of aircraft multistage booster jet engine reduces 350 degrees celsius. The thrust can be increased by 23% under the same oil quantity condition, and the temperature of the tail jet can be reduced by 357 ℃.
The principles and embodiments of the present invention have been described in this specification with reference to specific examples, the description of which is only for the purpose of aiding in understanding the method of the present invention and its core ideas; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In summary, the present description should not be construed as limiting the invention.
Claims (7)
1. A method for improving the performance of an aircraft multi-stage supercharged jet engine, characterized by: the method comprises the following steps:
s1, when the assembled multi-stage booster jet engine is tested, adjusting the power of the multi-stage booster jet engine to a first power for operation, and continuously filling diamond gravel at the front end of the multi-stage booster jet engine;
s2, stopping filling the diamond grit, regulating the power of the multi-stage booster jet engine to a second power, wherein the second power is higher than the first power, continuously filling the diamond grit at the front end of the multi-stage booster jet engine, and the grain size of the diamond grit in S2 is smaller than that of the diamond grit in S1;
s3, stopping filling diamond gravel, and adjusting the power of the multi-stage booster jet engine to be operated at a third power, wherein the third power is higher than the second power, and the front end of the multi-stage booster jet engine is not added at all;
s4, adjusting the power of the multi-stage booster jet engine to a second power operation, and continuously filling high-temperature alloy powder into the front end of the multi-stage booster jet engine;
s5, stopping filling the high-temperature alloy powder, keeping the multi-stage supercharged jet engine to run at the second power, and continuously filling the high-temperature resistant and wear-resistant powder at the front end of the multi-stage supercharged jet engine.
2. The method for improving the performance of an aircraft multi-stage supercharged jet engine of claim 1 wherein: the first power is 75%, the second power is 85%, and the third power is 95%.
3. The method for improving the performance of an aircraft multi-stage supercharged jet engine of claim 1 wherein: in S1, the diamond grit particle size was 50 microns and 0.4 kg/min was continuously charged for 80 minutes.
4. A method of improving the performance of an aircraft multi-stage booster jet engine according to claim 3, characterized by: in S2, the diamond grit particle size was 20 microns, and 0.25 kg/min was continuously charged for 80 minutes.
5. The method for improving the performance of an aircraft multi-stage supercharged jet engine of claim 1 wherein: in S4, the superalloy powder had a particle size of 5 microns and was added at 0.15 kg/min for 80 minutes.
6. The method for improving the performance of an aircraft multi-stage supercharged jet engine of claim 1 wherein: in S5, the high temperature resistant and abrasion resistant powder is zirconia powder.
7. The method for improving the performance of an aircraft multi-stage supercharged jet engine of claim 1 wherein: in S5, the particle size of the high-temperature-resistant and wear-resistant powder is 1-2 microns, and 0.1 kg/min is continuously filled for 150 minutes.
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