CN113049256A - High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine - Google Patents
High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine Download PDFInfo
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- CN113049256A CN113049256A CN201911378205.2A CN201911378205A CN113049256A CN 113049256 A CN113049256 A CN 113049256A CN 201911378205 A CN201911378205 A CN 201911378205A CN 113049256 A CN113049256 A CN 113049256A
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- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The invention discloses a high-temperature high-speed flame flow generating device for simulating the service environment of an aircraft engine, which relates to the technical field of the service environment simulation of the aircraft engine and can comprise a plasma torch, wherein the plasma torch is connected with a spray pipe, and the end part of the spray pipe is provided with a nozzle; the plasma torch comprises a heating system for providing a plasma flame jet, an etching substance supply system for injecting an etching medium into the plasma flame jet; the heating system and the corrosive substance supply system are connected with a control device. The invention can realize the simulation of the high-temperature, high-heat-flow-density and corrosion service environment of the thermal barrier coating, and provides an important experimental platform for effectively evaluating the performance and failure mechanism of the thermal barrier coating and the high-temperature structural material in the complex service environment.
Description
Technical Field
The invention relates to the technical field of aero-engine service environment simulation, in particular to a high-temperature high-speed flame flow generating device for simulating an aero-engine service environment.
Background
The aero-engine has been known as "pearl on crown" for a long time, and the development level thereof represents a national comprehensive technological level and national defense strength. The thrust-weight ratio of an aircraft engine is one of important indexes for measuring the performance of the engine, and is closely related to the maneuverability and the economy of an airplane. According to the carnot cycle principle, increasing the turbine front intake air temperature is the most important and feasible way to increase the thrust-to-weight ratio of the engine. At present, three common methods for increasing the front inlet air temperature of the turbine are as follows: develops a novel high-temperature structural material, an air film cooling technology and a thermal barrier coating technology. At present, the development of the traditional single crystal high temperature alloy and air film cooling technology is close to the limit of materials and processes, and the thermal barrier coating technology becomes the most feasible method for further increasing the temperature in front of the turbine.
The working environment of the aeroengine is extremely complex and severe, and comprises the effects of more than 20 loads such as high temperature, stress, corrosion environment and the like. Research shows that high-temperature oxidation, ablation, thermal expansion mismatch, particle erosion, corrosive substance erosion and the like are main reasons causing the failure of the thermal barrier coating. The early failure of the thermal barrier coating caused by various reasons is a key bottleneck for limiting the application development of the coating, an engine service environment simulation platform is established, the failure mechanism of the thermal barrier coating under various conditions is deeply researched, and the improvement and development of the thermal barrier coating based on the simulation platform is a necessary way for breaking the bottleneck.
At present, the work of simulating the service environment of some aero-engines at home and abroad is carried out, and the work mainly comprises coating thermal cycle, thermal gradient, corrosion environment, heat, force, environment coupling and the like. Flood circulation et al (patent No. CN1818612A) proposes a thermal barrier coating thermal shock resistance device based on high-temperature resistance furnace heating, Yangli et al (patent publication No. CN103091237B) proposes a high-temperature flame spray gun device for simulating a thermal barrier coating corrosion service environment, Wanrejun et al (patent publication No. CN105865961A) proposes a thermal shock experimental device based on a thermal barrier coating of an oxygen propane gas heating gun in a high-temperature, thermal gradient and CMAS coupling service environment, and Gongnaokui et al (patent publication No. CN 169994) discloses a service environment simulating thermal barrier coating heat, force and corrosion by coupling a corrosion environment and a material mechanical property experimental device of infrared rapid heating equipment. It can be found that the existing service environment simulation device is mostly based on fuel oil and gas combustion flame heating or resistance heating, the heating speed is slow, and the heating temperature is low; the service environment of the aircraft engine has the characteristics of high temperature, high temperature gradient, high heat flux density, rapid temperature rise and reduction, high-speed particle erosion and the like, and the conditions are difficult to realize simultaneously by the conventional simulation equipment.
Therefore, it is desirable to provide a new high-temperature and high-speed flame flow generating device for simulating the service environment of an aircraft engine to solve the above problems in the prior art.
Disclosure of Invention
The invention aims to provide a high-temperature high-speed flame flow generating device for simulating the service environment of an aircraft engine, which is used for solving the problems in the prior art, can realize the simulation of the high-temperature, high-heat-flow-density and corrosive service environment of a thermal barrier coating, and provides an important experimental platform for effectively evaluating the performance and failure mechanism of the thermal barrier coating and a high-temperature structural material in the complex service environment.
In order to achieve the purpose, the invention provides the following scheme: the invention provides a high-temperature high-speed flame flow generating device for simulating the service environment of an aircraft engine, which comprises a plasma torch, wherein the plasma torch is connected with a spray pipe, and the end part of the spray pipe is provided with a nozzle; the plasma torch comprises a heating system for providing a plasma flame jet, an etching substance supply system for injecting an etching medium into the plasma flame jet; the heating system and the corrosive substance supply system are connected with a control device.
Preferably, the heating system comprises a combustion chamber, the combustion chamber is provided with a working gas injection port, a power supply cathode and a first anode, and the working gas injection port is used for injecting working gas into the combustion chamber of the plasma torch; the working gas is ionized between the power supply cathode and the first anode to form the plasma flame jet.
Preferably, a second anode is further disposed behind the working gas injection port.
Preferably, the plasma torch further comprises a gas mixing chamber, the rear part of the combustion chamber is connected with the gas mixing chamber, and the gas mixing chamber is connected with the spray pipe; and a compressed air injection port is arranged on the air mixing chamber.
Preferably, the corrosive medium supply system comprises a liquid injection port and a powder feeding port, wherein the liquid injection port is arranged at the joint of the gas mixing chamber and the spray pipe and is used for injecting a liquid corrosive medium; the powder feeding port is arranged at the outlet of the nozzle and is used for injecting solid particle corrosive medium.
Preferably, the liquid corrosive medium comprises a sea salt solution, kerosene or CMAS suspension, and the solid particle corrosive medium comprises CMAS solid particles or Al2O3Solid particles.
Preferably, the number of the liquid injection ports is four, and the four liquid injection ports are uniformly distributed along the circumferential direction of the joint of the gas mixing chamber and the spray pipe.
Preferably, the cooling system is used for cooling the combustion chamber and the nozzle.
Preferably, the cooling system comprises a cooling channel, a cold water inlet and a cold water outlet are arranged at two ends of the cooling channel, and the cooling channel is arranged around the combustion chamber or the spray pipe.
Compared with the prior art, the invention has the following technical effects:
the invention adopts plasma flame jet as heat source, can quickly raise the temperature of the sample to a target value from 25 ℃ to 1200 ℃ within 10s, and has the power of up to 150MW/m2The heat flux density of the engine can simulate the service environment with high heat flux density and rapid temperature rise and fall of the engine more truly; the outlet gas of the invention has fast flow rate, and the erosion rate of solid particles added into plasma flame jet can reach 500 m/s; the temperature of the plasma torch flame can reach 3500 ℃, and in the future, the temperature of the plasma torch flame can reach 3500 DEGThe method is used for evaluating and testing the high-temperature performance of the novel thermal barrier coating and the ultrahigh-temperature structural material; the CMAS suspension, the sea salt solution and the aviation kerosene solution can be injected into plasma flame jet flow through atomization by utilizing compressed air, so that various corrosion environments of the aero-engine can be simulated, and conditions such as high temperature, high heat flow density, high temperature gradient, high speed particle erosion and the like can be coupled, so that the effective simulation of the complex service environment of the aero-engine can be realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a high-temperature high-speed flame flow generating device for simulating the service environment of an aircraft engine according to the invention;
wherein, 1 is a power cathode, 2 is a first anode, 3 is a second anode, 4 is a gas mixing chamber, 5 is a liquid injection port, 6 is a spray pipe, 7 is a spray nozzle, 8 is a powder feeding port, 9 is a first cooling channel, 11 is a second cooling channel, 12 is a third cooling channel, 10 is an air injection port, and 13 is a working gas injection port.
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.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
As shown in fig. 1, the present embodiment provides a high-temperature and high-speed flame flow generating device for simulating the service environment of an aircraft engine, which includes a plasma torch, a nozzle 6 connected to the plasma torch, and a nozzle 7 arranged at the end of the nozzle 6; the plasma torch comprises a heating system for providing a plasma flame jet, an etching substance supply system for injecting an etching medium into the plasma flame jet; the heating system and the corrosive substance supply system are connected with a control device.
In this embodiment, the heating system comprises a combustion chamber, the combustion chamber is provided with a working gas injection port 13, a power cathode 1 and a first anode 2, the working gas injection port 13 is used for injecting working gas into the combustion chamber of the plasma torch; the working gas is ionized between the power cathode 1 and the first anode 2 to form the plasma flame jet; a second anode 3 is provided behind the working gas inlet 13.
Specifically, the working gas of the heating system is air, plasma flame jet flow with different temperatures and speeds can be provided by adjusting the current voltage and the gas flow of the working power supply, a sample is rapidly heated to a high-temperature environment for simulation under the condition of high heat flow density, thermal cycle simulation under the condition of certain temperature gradient can be carried out, and closed-loop accurate control of the temperature is realized under the combined action of the temperature testing device and the control device. The surface temperature of the sample is tested by an infrared thermometer, the back surface temperature is tested by a K-type thermocouple, the front surface of the sample is heated by flame, and the back surface of the sample is cooled by compressed air, so that a certain temperature gradient can be formed on the surface and the back surface of the sample. The control device adopts the existing controller, such as a computer or a PLC (programmable logic controller) and the like, is used for testing with an infrared thermometer and a K-type thermocouple, and controls the current voltage and the gas flow of the working power supply and the control valve of the cooling spray pipe 6 according to the received temperature signal.
In this embodiment, the plasma torch further includes a gas mixing chamber 4, the gas mixing chamber 4 is connected to the rear of the combustion chamber, the gas mixing chamber 4 is connected to the nozzle 6, and the gas mixing chamber 4 is provided with a compressed air injection port 10. Specifically, the nozzle tube 6 of the nozzle 7 is connected with the plasma torch by screws, and nozzles 7 with different diameters are adopted according to the sample size and the heat flux density requirement, wherein the diameters are 8mm, 15mm, 20mm, 25mm and the like.
In the embodiment, the corrosive medium supply system comprises a liquid injection port 5 and a powder feeding port 8, wherein the liquid injection port 5 is arranged at the joint of the gas mixing chamber 4 and the spray pipe 6 and is used for injecting a liquid corrosive medium; the powder feeding port 8 is arranged at the outlet of the nozzle 7 and is used for injecting solid particle corrosive medium. Specifically, the liquid corrosion medium comprises a sea salt solution, kerosene or CMAS suspension, and the solid particle corrosion medium comprises CMAS solid particles or Al2O3Solid particles.
The number of the liquid injection ports 5 is four, and the four liquid injection ports 5 are uniformly distributed along the joint of the gas mixing chamber 4 and the spray pipe 6 in a circumferential manner.
In this embodiment, an atomizing nozzle 7 is arranged on the liquid injection port 5, the atomizing nozzle 7 is connected with a liquid inlet pipe, a corrosive medium supply system can input CMAS suspension, sea salt solution and aviation kerosene solution through the liquid inlet pipe, the CMAS suspension, the sea salt solution and the aviation kerosene solution are atomized by the atomizing nozzle 7 and injected into plasma flame jet by compressed air, the adding amount of the liquid corrosive medium is controlled by a corrosion-resistant ZB-3WB glass rotameter (or other corrosion-resistant liquid flow meters meeting the requirements) arranged at the liquid injection port 5, and the pressure of the compressed air is adjusted by a pressurizing valve arranged at the air injection port 10, so that various corrosion environments of the aircraft engine can be simulated; the etching medium supply system may supply Al having different particle diameters2O3The particles are injected into the plasma flame via compressed air, simulating an environment in which the thermal barrier coating and engine blades are eroded and eroded by high temperature, high velocity particles.
In the embodiment, when the plasma torch works, firstly, the power of the plasma torch is selected, the working gas-air of the plasma torch enters the plasma torch from the working gas injection port 13, the high-speed plasma flame jet is formed by ionization between the power cathode 1 and the first anode 2, the plasma flame jet is amplified and stabilized through the second anode 3, enters the gas mixing chamber 4, is mixed with the compressed air injected through the compressed air injection port 10, is compressed through the spray pipe 6 and is sprayed out from the nozzle 7.
Corrosive substances such as sea salt solution and kerosene solution are injected into the plasma flame flow through a liquid injection port 5 at the joint of the gas mixing chamber 4 and the nozzle 6, and CMAS and Al can be injected through a powder feeding port 8 at the outlet of the nozzle 72O3When solid particles are injected into the flame, the high-speed plasma flame flow carries corrosive substances to the surface of the sample, and the experimental sample is heated, impacted and corroded.
In the present embodiment, it also comprises a cooling system for cooling the combustion chamber and the lance 6; the cooling system comprises a cooling channel, a cold water inlet and a cold water outlet are arranged at two ends of the cooling channel, and the cooling channel is arranged around the combustion chamber or the spray pipe 6. Specifically, the cooling channels include a third cooling channel 12 and a second cooling channel 11 which are arranged at the combustion chamber and a first cooling channel 9 which is arranged at the spray pipe 6, and cooling is realized by introducing cooling water from a cold water inlet and flowing out from a cold water outlet.
In the embodiment, the cooling system carries out circulating water cooling on the combustion chamber and the nozzle 7 when in work, a cooling spray pipe 6 is arranged at the back of the sample, the cooling spray pipe 6 is connected with an air source through a control valve and is used for spraying compressed air, and the back of the sample is cooled through the compressed air to simulate a service environment with gradient temperature; after heating is finished, the compressed air quickly cools the sample to achieve the condition of simulating thermal cycle;
the control device is connected with the heating system, the cooling system and the corrosive medium supply system, and realizes the simulation of high temperature, high heat flux density, gradient temperature, various corrosive environments and particle erosion environments.
The invention adopts plasma flame as heat source, can quickly raise the temperature of the sample to a target value from 25 ℃ to 1200 ℃ within 10s, and has the power of up to 150MW/m2The heat flux density of the engine can simulate the service environment with high heat flux density and rapid temperature rise and fall of the engine more truly;the outlet gas flow rate of the plasma torch is high, and the erosion rate of solid particles added into the plasma flame flow can reach 500 m/s; the plasma flame temperature can reach 3500 ℃, and the plasma flame temperature can be used for evaluating and testing the high-temperature performance of a novel thermal barrier coating and an ultrahigh-temperature structural material in the future; the CMAS suspension, the sea salt solution and the aviation kerosene solution can be injected into plasma flame jet flow through atomization by utilizing compressed air, so that various corrosion environments of the aero-engine can be simulated, and conditions such as high temperature, high heat flow density, high temperature gradient, high speed particle erosion and the like can be coupled, so that the effective simulation of the complex service environment of the aero-engine can be realized. The invention can become an important experimental platform for evaluating the performance of the thermal barrier coating and the high-temperature structural material in the service environment of the engine and researching the failure mechanism of the thermal barrier coating and the high-temperature structural material.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. The utility model provides a high temperature high speed flame flows generating device of simulation aeroengine service environment which characterized in that: the plasma torch is connected with a spray pipe, and a nozzle is arranged at the end part of the spray pipe; the plasma torch comprises a heating system for providing a plasma flame jet, an etching substance supply system for injecting an etching medium into the plasma flame jet; the heating system and the corrosive substance supply system are connected with a control device.
2. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 1, wherein: the heating system comprises a combustion chamber, wherein a working gas injection port, a power supply cathode and a first anode are arranged on the combustion chamber, and the working gas injection port is used for injecting working gas into the combustion chamber of the plasma torch; the working gas is ionized between the power supply cathode and the first anode to form the plasma flame jet.
3. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 2, wherein: and a second anode is also arranged behind the working gas injection port.
4. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 2, wherein: the plasma torch also comprises a gas mixing chamber, the rear part of the combustion chamber is connected with the gas mixing chamber, and the gas mixing chamber is connected with the spray pipe; and a compressed air injection port is arranged on the air mixing chamber.
5. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 4, wherein: the corrosive medium supply system comprises a liquid injection port and a powder feeding port, wherein the liquid injection port is arranged at the joint of the gas mixing chamber and the spray pipe and is used for injecting a liquid corrosive medium; the powder feeding port is arranged at the outlet of the nozzle and is used for injecting solid particle corrosive medium.
6. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 5, wherein: the liquid corrosive medium comprises a sea salt solution, kerosene or CMAS suspension, and the solid particle corrosive medium comprises CMAS solid particles or Al2O3Solid particles.
7. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 5, wherein: the liquid injection openings are four and are circumferentially and uniformly distributed along the joint of the gas mixing chamber and the spray pipe.
8. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 1, wherein: the cooling system is used for cooling the combustion chamber and the spray pipe.
9. The device for generating high-temperature and high-speed flame flow for simulating the service environment of an aircraft engine as claimed in claim 8, wherein: the cooling system comprises a cooling channel, a cold water inlet and a cold water outlet are arranged at two ends of the cooling channel, and the cooling channel is arranged around the combustion chamber or the spray pipe.
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| CN201911378205.2A CN113049256A (en) | 2019-12-27 | 2019-12-27 | High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine |
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| CN201911378205.2A CN113049256A (en) | 2019-12-27 | 2019-12-27 | High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114047090A (en) * | 2022-01-11 | 2022-02-15 | 矿冶科技集团有限公司 | Method for accurately positioning high-jet flame thermal shock test sample and high-jet flame thermal shock test method |
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2019
- 2019-12-27 CN CN201911378205.2A patent/CN113049256A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114047090A (en) * | 2022-01-11 | 2022-02-15 | 矿冶科技集团有限公司 | Method for accurately positioning high-jet flame thermal shock test sample and high-jet flame thermal shock test method |
| CN114047090B (en) * | 2022-01-11 | 2022-04-01 | 矿冶科技集团有限公司 | Method for accurately positioning high-jet flame thermal shock test sample and high-jet flame thermal shock test method |
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