A method and system for determining the concentration of a corrosion medium for simulating an aeroengine

Abstract

The present invention discloses a method and system for determining the concentration of a corrosive medium for simulating an aero-engine, which relates to the field of aero-engine service simulation. The method includes: based on the ideal gas state formula, obtaining the gas density at the air inlet of the aero-engine according to the gas pressure, gas temperature, gas density before the air inlet and the gas pressure, gas temperature at the air inlet, and obtaining the concentration of the corrosive medium in the gas at the air inlet of the aero-engine according to the gas pressure, gas temperature, concentration of the corrosive medium in the gas before the air inlet and the gas pressure, gas temperature at the air inlet; the gas density at the air inlet and the concentration of the corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied. The present invention solves the problem that it is difficult to quantitatively apply the corrosive medium when the aero-engine simulation test device simulates the service of the thermal barrier coating of the aero-engine turbine blade.

Description

Technical Field

[0001] The present invention relates to the field of aero-engine service simulation, and particularly to a method and system for determining the concentration of a corrosion medium for simulating an aero-engine. Background Art

[0002] With the continuous development of aviation technology, the speed and range of aircraft are also constantly increasing, and aero-engines are developing towards higher thrust-to-weight ratios, flow ratios, and turbine inlet temperatures. Therefore, it has become difficult to meet the service requirements of engine blades solely by improving the performance of superalloys themselves, and it is necessary to prepare high-performance thermal barrier coatings on their surfaces. Thermal barrier coatings, together with blade cooling design and single-crystal superalloy material technology, are one of the three core technologies for advanced aero-engine blades. Aero-engine turbine blades are faced with the combined action of complex environments such as high temperature, high temperature gradient, high heat flux density, rapid heating and cooling, and corrosion media during service. For a long time, the assessment and evaluation of the service performance of blade thermal barrier coatings in China have mainly relied on engine tests. However, engine tests consume huge human, time, and material costs, and it is difficult to obtain process information through this assessment method. Therefore, different test devices have been built for the complex service environment of aero-engine turbine blades (Patent Publication No.: CN113654976A; CN113484020A; CN113176297A), and the service evolution process of the microstructure and microdefects of the thermal barrier coatings of aero-engine blades under near-operating conditions has been obtained, thus providing a key test means for determining the key factors affecting the performance and life of the coatings.

[0003] In addition to failure modes such as ceramic layer sintering, erosion, and bond coat oxidation during the service of the thermal barrier coating on the turbine blade of an aeroengine, high-temperature corrosion is also an important cause of the failure of the thermal barrier coating. During the actual service of an aircraft, the engine will intake a large amount of particulate corrosion media such as dust, volcanic ash, runway debris, and PM2.5. In addition to being affected by particulate corrosion media, in a marine environment, especially for carrier-based aircraft, during frequent takeoffs and landings on the sea surface in a high-temperature, high-humidity, and high-salt environment, the thermal barrier coating faces the challenge of corrosion by marine atmospheric media. The intrusion of salts (such as sulfate and chloride salts) in marine air and particles (dust, volcanic ash, runway debris, PM2.5) in the atmospheric environment into the hot-end components of the turbine is the main cause of thermal corrosion damage. Currently, among the patents of disclosed simulation test devices, Yang Li et al. disclosed a test device for simulating and real-time testing the gas corrosion failure of a thermal barrier coating (patent publication number: CN103091239A); Qian Shengjie et al. disclosed a test device for simulating and real-time testing the gas corrosion failure of a thermal barrier coating (patent authorization announcement number: CN212540075U); Zhou Yichun et al. disclosed a test device for simulating the service environment of a thermal barrier coating and real-time detecting its failure (patent publication number: CN103091189B), but the above test devices did not mention the concentration of the gas applied during the simulation process. In the same year, Zhou Yichun et al. also disclosed a test device for simulating and real-time testing the high-temperature deposit corrosion of a thermal barrier coating (patent publication number: CN103063563B), where the particle flow rate is 0 - 250 g / min. However, in the simulation process mentioned in the above test devices, the concentration of the corrosion medium applied is not calculated according to the actual service conditions, resulting in the test device being unable to truly simulate the service environment of an aeroengine near the working conditions, and thus unable to accurately predict and analyze the service life and failure mechanism of the thermal barrier coating.

[0004] Therefore, there is an urgent need for a method for determining the concentration of the corrosion medium for simulating an aeroengine to solve the problem that it is difficult to quantitatively apply the corrosion medium when the aeroengine simulation test device simulates the service of the thermal barrier coating on the turbine blade of an aeroengine. Summary of the Invention

[0005] Based on this, the embodiments of the present invention provide a method and system for determining the concentration of the corrosion medium for simulating an aeroengine, which can truly simulate the concentration of the corrosion medium during the service of an aeroengine, and solve the problem that it is difficult to quantitatively apply the corrosion medium when the aeroengine simulation test device simulates the service of the thermal barrier coating on the turbine blade of an aeroengine.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] A method for determining the concentration of the corrosion medium for simulating an aeroengine includes:

[0008] Obtain the first data and the second data of the aeroengine; the first data includes: the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the concentration of the corrosive medium in the gas before the air inlet; the second data includes: the gas pressure at the air inlet and the gas temperature at the air inlet;

[0009] According to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state formula, obtain the gas density at the air inlet of the aeroengine;

[0010] According to the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, the second data, and the ideal gas state formula, obtain the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; the gas density at the air inlet and the concentration of the corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied;

[0011] Wherein, the flow rate of the corrosive medium to be applied is the flow rate of the corrosive medium applied when simulating the thermal barrier coating of the turbine blade of the aeroengine by using the aeroengine simulation test device.

[0012] Optionally, the obtaining of the gas density at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state formula specifically includes:

[0013] Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the second data into the density calculation formula to obtain the gas density at the air inlet of the aeroengine; the density calculation formula is determined according to the ideal gas state formula; the density calculation formula is:

[0014]

[0015] Wherein, ρ 空气1 is the gas density before the air inlet of the aeroengine; ρ 空气2 is the gas density at the air inlet of the aeroengine; P1 is the gas pressure before the air inlet of the aeroengine; P2 is the gas pressure at the air inlet of the aeroengine; T1 is the gas temperature before the air inlet of the aeroengine; T2 is the gas temperature at the air inlet of the aeroengine.

[0016] Optionally, obtaining the concentration of the corrosive medium in the gas at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, the second data, and the ideal gas state equation specifically includes:

[0017] Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, and the second data into the concentration calculation formula to obtain the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; the concentration calculation formula is determined according to the ideal gas state equation; the concentration calculation formula is:

[0018]

[0019] where ρ 介质1 is the concentration of the corrosive medium in the gas before the air inlet of the aeroengine; ρ 介质2 is the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; P1 is the gas pressure before the air inlet of the aeroengine; P2 is the gas pressure at the air inlet of the aeroengine; T1 is the gas temperature before the air inlet of the aeroengine; T2 is the gas temperature at the air inlet of the aeroengine.

[0020] Optionally, the method for determining the flow rate of the corrosive medium to be applied by using the gas density at the air inlet and the concentration of the corrosive medium in the gas at the air inlet is:

[0021] Obtain the air mass flow rate at the air inlet of the aeroengine;

[0022] Calculate the air volume flow rate at the air inlet according to the air mass flow rate at the air inlet and the gas density at the air inlet;

[0023] Determine the product of the air volume flow rate at the air inlet and the concentration of the corrosive medium in the gas at the air inlet as the flow rate of the corrosive medium to be applied.

[0024] Optionally, the corrosive medium in the gas is salt in marine atmosphere or particles in atmospheric environment.

[0025] Optionally, the salt in the marine atmosphere includes at least one of sulfate in the marine atmosphere and chloride salt in the marine atmosphere.

[0026] Optionally, the particles in the atmospheric environment include at least one of atmospheric dust, volcanic ash, runway debris, and PM2.5.

[0027] The present invention also provides a corrosion medium concentration determination system for simulating an aeroengine, including:

[0028] A data acquisition module for acquiring first data and second data of an aeroengine; the first data includes: gas pressure before the air inlet, gas temperature before the air inlet, gas density before the air inlet, and concentration of corrosive medium in the gas before the air inlet; the second data includes: gas pressure at the air inlet and gas temperature at the air inlet;

[0029] A gas density calculation module for obtaining the gas density at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state formula;

[0030] A medium concentration calculation module for obtaining the concentration of corrosive medium in the gas at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of corrosive medium in the gas before the air inlet, the second data, and the ideal gas state formula; the gas density at the air inlet and the concentration of corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied;

[0031] Wherein, the flow rate of the corrosive medium to be applied is the flow rate of the corrosive medium applied when simulating the thermal barrier coating of the turbine blade of the aeroengine by using the aeroengine simulation test device.

[0032] Compared with the prior art, the beneficial effects of the present invention are:

[0033] The embodiment of the present invention provides a method and system for determining the concentration of corrosive medium for simulating an aeroengine. Based on the ideal gas state formula, the gas density at the air inlet of the aeroengine is obtained according to the gas pressure, gas temperature, gas density before the air inlet, and the gas pressure and gas temperature at the air inlet. The concentration of corrosive medium in the gas at the air inlet of the aeroengine is obtained according to the gas pressure, gas temperature, concentration of corrosive medium in the gas before the air inlet, and the gas pressure and gas temperature at the air inlet. The gas density at the air inlet and the concentration of corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied. The present invention can truly simulate the concentration of corrosive medium during the service of an aeroengine, and solves the problem that it is difficult to quantitatively apply corrosive medium when the aeroengine simulation test device simulates the service of the thermal barrier coating of the turbine blade of the aeroengine. Description of the Drawings

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0035] Figure 1 The flowchart of the method for determining the concentration of corrosive medium for simulating an aero - engine provided by an embodiment of the present invention;

[0036] Figure 2 The structural diagram of the system for determining the concentration of corrosive medium for simulating an aero - engine provided by an embodiment of the present invention. Detailed implementation manners

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] To make the above - mentioned objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific implementation manners.

[0039] Figure 1 The flowchart of the method for determining the concentration of corrosive medium for simulating an aero - engine provided by an embodiment of the present invention. Refer to Figure 1 , the method includes:

[0040] Step 101: Obtain the first data and the second data of the aero - engine; the first data includes: the gas pressure before the intake port, the gas temperature before the intake port, the gas density before the intake port, and the concentration of the corrosive medium in the gas before the intake port; the second data includes: the gas pressure at the intake port and the gas temperature at the intake port.

[0041] Step 102: Obtain the gas density at the intake port of the aero - engine according to the gas pressure before the intake port, the gas temperature before the intake port, the gas density before the intake port, the second data, and the ideal gas state formula.

[0042] Step 103: Obtain the concentration of the corrosive medium in the gas at the intake port of the aero - engine according to the gas pressure before the intake port, the gas temperature before the intake port, the concentration of the corrosive medium in the gas before the intake port, the second data, and the ideal gas state formula; the gas density at the intake port and the concentration of the corrosive medium in the gas at the intake port are used to determine the flow rate of the corrosive medium to be applied.

[0043] Wherein, the flow rate of the corrosive medium to be applied is the flow rate of the corrosive medium applied when simulating the thermal barrier coating of the turbine blade of the aero - engine by using an aero - engine simulation test device.

[0044] In one example, step 102 specifically includes:

[0045] Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the second data into the density calculation formula to obtain the gas density at the air inlet of the aeroengine; the density calculation formula is determined according to the ideal gas state formula; the density calculation formula is:

[0046]

[0047] where ρ 空气1 is the gas density before the air inlet of the aeroengine; ρ 空气2 is the gas density at the air inlet of the aeroengine; P1 is the gas pressure before the air inlet of the aeroengine; P2 is the gas pressure at the air inlet of the aeroengine; T1 is the gas temperature before the air inlet of the aeroengine; T2 is the gas temperature at the air inlet of the aeroengine.

[0048] Step 103 specifically includes:

[0049] Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, and the second data into the concentration calculation formula to obtain the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; the concentration calculation formula is determined according to the ideal gas state formula; the concentration calculation formula is:

[0050]

[0051] where ρ 介质1 is the concentration of the corrosive medium in the gas before the air inlet of the aeroengine; ρ 介质2 is the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; P1 is the gas pressure before the air inlet of the aeroengine; P2 is the gas pressure at the air inlet of the aeroengine; T1 is the gas temperature before the air inlet of the aeroengine; T2 is the gas temperature at the air inlet of the aeroengine.

[0052] The determination process of the above density calculation formula and concentration calculation formula is as follows:

[0053] Determine the ideal gas state formula, as shown in formula (1):

[0054] PV = nRT (1)

[0055] where P represents pressure, with the unit of Pa; V represents gas volume, with the unit of m 3; n represents the amount of gas substance (gas mass divided by the molar mass of the gas), with the unit of mol; T represents the gas temperature, with the unit of K (Kelvin); R represents the gas constant (8.314), with the unit of J·mol -1 ·K -1 or kPa·L·mol -1 ·K -1 .

[0056] Formulating the formula (1) gives formula (2):

[0057]

[0058] Among them, m represents the gas mass, with the unit of g; ρ is the density, with the unit of kg·m 3 ; M represents the molar mass, with the unit of g·mol -1 ; Canceling out m gives formula (3):

[0059]

[0060] From formula (3), the ideal gas state formulas before the inlet of the aero-engine and at the inlet of the aero-engine can be obtained as formulas (4) and (5) respectively:

[0061]

[0062]

[0063] Among them, P1 is the gas pressure before the inlet of the aero-engine; P2 is the gas pressure at the inlet of the aero-engine; ρ1 is the substance density or concentration before the inlet of the aero-engine (depending on different application scenarios, this can be the gas density or the concentration of the corrosive medium in the gas), ρ2 is the substance density or concentration at different inlets of the aero-engine (depending on different application scenarios, this can be the gas density or the concentration of the corrosive medium in the gas); T1 is the gas temperature before the inlet of the aero-engine; T2 is the gas temperature at the inlet of the aero-engine; M1 and M2 are the gas molar masses before the inlet of the aero-engine and at different inlets of the aero-engine respectively. Since the gas before the inlet of the aero-engine and at different inlets of the aero-engine is the same gas, according to the law of conservation of mass, M1 = M2. Formula (4) is formulated into formula (6):

[0064]

[0065] Substituting formula (6) into formula (5) and organizing gives formula (7):

[0066]

[0067] Since ρ1, T1, P1, P2, and T2 are known, the substance density or concentration ρ2 at different air inlets of the aeroengine can be obtained.

[0068] Thus, according to formula (7), the density calculation formula and the concentration calculation formula can be obtained.

[0069] After step 103, it further includes:

[0070] Determine the flow rate of the corrosion medium to be applied by using the gas density at the air inlet and the concentration of the corrosion medium in the gas at the air inlet. The specific method is as follows:

[0071] Obtain the air mass flow rate S at the air inlet of the aeroengine m ; According to the gas density at the air inlet, convert the air mass flow rate S at the air inlet m into the air volume flow rate S at the air inlet v ; Determine the product of the air volume flow rate S at the air inlet and the concentration of the corrosion medium in the gas at the air inlet as the flow rate of the corrosion medium to be applied, that is, obtain the flow rate S of the corrosion medium that should be applied when simulating the thermal barrier coating of the aeroengine turbine blade by using the aeroengine simulation test device. v

[0072] In this embodiment, the corrosion medium in the gas is salt in marine atmosphere or particles in the atmospheric environment. The salt in marine atmosphere includes at least one of sulfate in marine atmosphere and chloride salt in marine atmosphere. The particles in the atmospheric environment include at least one of atmospheric dust, volcanic ash, runway debris, and PM2.5.

[0073] In this embodiment, according to the gas density in front of the aeroengine air inlet, the concentration of the corrosion medium in the environment, and the actual temperatures and pressures in front of the aeroengine air inlet and at different air inlets, the gas density and the concentration of the corrosion medium entering different air inlets of the aeroengine are calculated. Furthermore, the flow rate of the corrosion medium that should be applied when simulating the thermal barrier coating of the aeroengine turbine blade by using the simulation test device is calculated. By using this method, the concentration of the corrosion medium during the service of the aeroengine can be truly simulated, the reliability of the simulation data using the simulation test device can be further improved, guidance can be provided for manufacturing long-life thermal barrier coating materials and coating structure design, and thus technical guarantee can be provided for the stability and reliability of the aeroengine.

[0074] For different application scenarios, the following will be further described in detail by taking the corrosion medium as PM2.5 in the atmospheric environment and the corrosion medium as salt in the marine atmosphere as examples respectively.

[0075] Specific example 1:

[0076] This example aims to solve the problem that it is difficult to accurately quantitatively analyze the concentration of applied corrosion particles when using an aero-engine simulation test device to simulate the engine's service. First, according to the ideal gas state formula (PV = nRT), the gas density and the concentration of corrosion particles at different air inlets are calculated using the pressure, temperature, gas density, concentration of corrosion particles in the environment before the aero-engine air inlet, and the pressure and temperature at different inlets of the aero-engine. Then, the mass flow rate at different air inlets is converted into a volume flow rate, and further, the flow rate of corrosion particles that should be applied when using the simulation test device to simulate the aero-engine service is calculated through the concentration of corrosion particles at different air inlets. Using this method, the concentration of corrosion particles during the aero-engine's service can be realistically simulated, further improving the authenticity of the simulation data obtained using the simulation test device. Specifically:

[0077] According to the typical state performance parameters of an aero-engine, under the medium-thrust state before the aero-plane takes off (altitude is 0 km), the gas pressures P1 and P2 at the front of the aero-engine air inlet and at the high-pressure turbine air inlet of the aero-engine are 101.33 kPa and 2252.71 kPa respectively, and the temperatures T1 and T2 at the front of the aero-engine air inlet and at the high-pressure turbine air inlet of the aero-engine are 288.15 K and 1619.84 K respectively. The gas density ρ at the front of the air inlet under the temperature of 288.15 K and pressure of 101.33 kPa 空气1 is 1.218 kg·m -3 , and the concentration ρ of PM2.5 in the gas at the front of the air inlet detected in Beijing in August 2022 介质1 is 20 μg·m -3 .

[0078] Substitute ρ 空气1 , T1, P1, P2, and T2 into the density calculation formula, and substitute ρ 介质1 , T1, P1, P2, and T2 into the concentration calculation formula. It can be obtained that under the medium-thrust state before the aero-plane takes off (altitude is 0 km), the gas density ρ 空气2 at the high-pressure turbine air inlet of the aero-engine is 4.817 kg·m -3 , and the concentration ρ of PM2.5 in the gas at the high-pressure turbine air inlet of the aero-engine 介质2 is 79.094 μg·m -3 .

[0079] Since the air mass flow rate S m at the high-pressure turbine air inlet of the aero-engine is 39.3240 kg·s -1 , therefore, the air volume flow rate S v at the air inlet is 8.164 m 3 .s -1, and then the flow rate S of the corrosion particles to be applied when simulating the thermal barrier coating of the aero-engine turbine blade using the above aero-engine simulation test device is 0.646 mg·s -1 .

[0080] Specific Example 2:

[0081] This example is to solve the problem that it is difficult to accurately quantitatively analyze the applied salt concentration when simulating the engine service using the aero-engine simulation test device. First, according to the ideal gas state formula (PV = nRT), the gas density and the salt concentration in the gas at different inlet ports of the aero-engine are calculated using the pressure, temperature, gas density, salt concentration in the gas before the aero-engine inlet, and the pressure and temperature at different inlet ports of the aero-engine. Then, the mass flow rate at different inlet ports is converted into a volume flow rate, and further, the flow rate of the salt-containing gas to be applied when simulating the aero-engine service using the simulation test device is calculated through the salt concentration in the gas at different inlet ports. Using this method, the salt concentration in the gas during the aero-engine service can be realistically simulated, and the authenticity of the simulation data using the simulation test device can be further improved. Specifically:

[0082] According to the typical aero-engine state performance parameters, under the medium-thrust state before the aero-plane takes off (altitude is 0 km), the gas pressures P1 and P2 at the front of the aero-engine inlet and at the high-pressure turbine inlet of the aero-engine are 101.33 kPa and 2252.71 kPa respectively, the temperatures T1 and T2 at the front of the aero-engine inlet and at the high-pressure turbine inlet of the aero-engine are 288.15 K and 1619.84 K respectively, and the gas density ρ at the front of the inlet port at a temperature of 288.15 K and a pressure of 101.33 kPa 空气1 is 1.218 kg·m -3 , and according to the detection of the wheat island monitoring station, the salt concentration ρ in the gas before the inlet port in March 2022 介质1 is 30.5 mg·m -3 .

[0083] Substitute ρ 空气1 , T1, P1, P2, and T2 into the density calculation formula, and substitute ρ 介质1 , T1, P1, P2, and T2 into the concentration calculation formula. It can be obtained that under the medium-thrust state before the aero-plane takes off (altitude is 0 km), the gas density ρ at the high-pressure turbine inlet of the aero-engine 空气2 is 4.817 kg·m -3 , and the salt concentration ρ in the gas at the high-pressure turbine inlet of the aero-engine 介质2 is 120.61 mg·m -3 .

[0084] Due to the air mass flow rate S at the high-pressure turbine inlet of the aero-engine m being 39.3240 kg / s -1 , the air volume flow rate S at the inlet is v 8.164 m 3 / s -1 . Furthermore, the flow rate S of the salt-containing gas to be applied when simulating the thermal barrier coating of the aero-engine turbine blade using the above aero-engine simulation test device is obtained as 0.985 g / s -1 .

[0085] To implement the above method to achieve the corresponding functions and technical effects, a corrosion medium concentration determination system for simulating an aero-engine is provided below Figure 2 The structural diagram of the corrosion medium concentration determination system for simulating an aero-engine provided by the embodiment of the present invention

[0086] Referring to Figure 2 , the system includes

[0087] A data acquisition module 201 for acquiring the first data and the second data of the aero-engine; the first data includes: the gas pressure before the inlet, the gas temperature before the inlet, the gas density before the inlet, and the concentration of the corrosion medium in the gas before the inlet; the second data includes: the gas pressure at the inlet and the gas temperature at the inlet

[0088] A gas density calculation module 202 for obtaining the gas density at the inlet of the aero-engine according to the gas pressure before the inlet, the gas temperature before the inlet, the gas density before the inlet, the second data, and the ideal gas state formula

[0089] A medium concentration calculation module 203 for obtaining the concentration of the corrosion medium in the gas at the inlet of the aero-engine according to the gas pressure before the inlet, the gas temperature before the inlet, the concentration of the corrosion medium in the gas before the inlet, the second data, and the ideal gas state formula; the gas density at the inlet and the concentration of the corrosion medium in the gas at the inlet are used to determine the flow rate of the corrosion medium to be applied

[0090] Wherein, the flow rate of the corrosion medium to be applied is the flow rate of the corrosion medium applied when simulating the thermal barrier coating of the turbine blade of the aero-engine using the aero-engine simulation test device

[0091] In the present specification, the various embodiments are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other. For the system disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple. For the relevant parts, reference can be made to the description in the method section.

[0092] In this article, specific examples are used to elaborate on the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation on the present invention.

Claims

1. A method for determining the concentration of corrosive medium for simulating an aero-engine, characterized in that Including: Obtain the first data and the second data of the aeroengine; the first data includes: the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the concentration of the corrosive medium in the gas before the air inlet; the second data includes: the gas pressure at the air inlet and the gas temperature at the air inlet; According to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state formula, obtain the gas density at the air inlet of the aeroengine; Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, and the second data into the concentration calculation formula to obtain the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; the concentration calculation formula is determined according to the ideal gas state formula; the concentration calculation formula is: where ρ 介质1 is the concentration of the corrosive medium in the gas before the air inlet of the aeroengine; ρ 介质2 is the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; P1 is the gas pressure before the air inlet of the aeroengine; P2 is the gas pressure at the air inlet of the aeroengine; T1 is the gas temperature before the air inlet of the aeroengine; T2 is the gas temperature at the air inlet of the aeroengine; the gas density at the air inlet and the concentration of the corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied; Wherein, the flow rate of the corrosive medium to be applied is the flow rate of the corrosive medium applied when simulating the thermal barrier coating of the turbine blade of the aeroengine by using the aeroengine simulation test device.

2. The method for determining the concentration of a corrosive medium for simulating an aeroengine according to claim 1, wherein The step of obtaining the gas density at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state formula specifically includes: Substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the second data into the density calculation formula to obtain the gas density at the air inlet of the aeroengine; the density calculation formula is determined according to the ideal gas state formula; the density calculation formula is: where ρ 空气1 is the gas density in front of the air inlet of the aero-engine; ρ 空气2 is the gas density at the air inlet of the aero-engine; P1 is the gas pressure in front of the air inlet of the aero-engine; P2 is the gas pressure at the air inlet of the aero-engine; T1 is the gas temperature in front of the air inlet of the aero-engine; T2 is the gas temperature at the air inlet of the aero-engine.

3. A method for determining the concentration of a corrosive medium for simulating an aeroengine according to claim 1, characterized in that, The method for determining the flow rate of the corrosive medium to be applied by using the gas density at the air inlet and the concentration of the corrosive medium in the gas at the air inlet is: Obtain the air mass flow rate at the air inlet of the aeroengine; Calculate the air volume flow rate at the air inlet according to the air mass flow rate at the air inlet and the gas density at the air inlet; Determine the product of the air volume flow rate at the air inlet and the concentration of the corrosive medium in the gas at the air inlet as the flow rate of the corrosive medium to be applied.

4. A method for determining the concentration of a corrosive medium for simulating an aeroengine according to claim 1, wherein The corrosive medium in the gas is salt in marine atmosphere or particles in atmospheric environment.

5. The method for determining the concentration of a corrosion medium for simulating an aeroengine according to claim 4, characterized in that, The salt in marine atmosphere includes at least one of sulfate in marine atmosphere and chloride salt in marine atmosphere.

6. The method for determining the concentration of a corrosion medium for simulating an aero-engine according to claim 4, wherein The particles in atmospheric environment include at least one of atmospheric dust, volcanic ash, runway debris, and PM2.

5.

7. A corrosion medium concentration determination system for simulating an aeroengine, characterized in that Including: A data acquisition module, configured to obtain the first data and the second data of the aeroengine; the first data includes: the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, and the concentration of the corrosive medium in the gas before the air inlet; the second data includes: the gas pressure at the air inlet and the gas temperature at the air inlet; A gas density calculation module, configured to obtain the gas density at the air inlet of the aeroengine according to the gas pressure before the air inlet, the gas temperature before the air inlet, the gas density before the air inlet, the second data, and the ideal gas state equation; A medium concentration calculation module, configured to substitute the gas pressure before the air inlet, the gas temperature before the air inlet, the concentration of the corrosive medium in the gas before the air inlet, and the second data into the concentration calculation formula to obtain the concentration of the corrosive medium in the gas at the air inlet of the aeroengine; the concentration calculation formula is determined according to the ideal gas state equation; the concentration calculation formula is: where ρ 介质1 is the concentration of the corrosive medium in the gas before the air inlet of the aero-engine; ρ 介质2 is the concentration of the corrosive medium in the gas at the air inlet of the aero-engine; P1 is the gas pressure before the air inlet of the aero-engine; P2 is the gas pressure at the air inlet of the aero-engine; T1 is the gas temperature before the air inlet of the aero-engine; T2 is the gas temperature at the air inlet of the aero-engine; the gas density and the concentration of the corrosive medium in the gas at the air inlet are used to determine the flow rate of the corrosive medium to be applied; wherein the flow rate of the corrosive medium to be applied is the flow rate of the corrosive medium applied during the simulation of the thermal barrier coating of the turbine blade of the aeroengine using the aeroengine simulation test device.

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