Calculation method and acquisition device for gas temperature field of aero-engine combustion chamber

Abstract

The invention discloses a calculation method and an acquisition device for a gas temperature field of a combustion chamber of an aero-engine. The aero-engine combustion chamber fuel gas temperature field-oriented calculation method comprises the following steps: acquiring a combustion reaction equilibrium formula according to components of combustion chamber fuel gas; calculating a residual gas coefficient alpha; calculating an oil-gas ratio f; calculating combustion efficiency eta; the enthalpy value I of combustion chamber outlet gas is calculated; and according to the calculated I value, the corresponding combustion temperature can be obtained by using an enthalpy value table. Therefore, the fuel gas temperature field of the combustion chamber of the aero-engine can be obtained, and key parameters such as temperature distribution, flow characteristics and combustion efficiency of fuel gas in the combustion chamber can be known.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine combustion chamber performance testing, and in particular to a calculation method and an acquisition device for a combustion chamber gas temperature field of an aero-engine combustion chamber. Background Art

[0002] The aircraft engine is the heart of the aircraft, and its performance is directly related to the flight performance, safety and economy of the aircraft. The combustion chamber, as one of the key components of the aircraft engine, undertakes the important task of converting the chemical energy in the fuel into thermal energy. The high-temperature gas in the combustion chamber not only provides the energy for the turbine and tail nozzle to do work, but also directly affects the thrust, efficiency and life of the engine. With the continuous development of aviation technology, the performance requirements of aircraft engines are getting higher and higher, especially the improvement of thrust and efficiency. As one of the important means to achieve this goal, the uniformity and stability of the internal gas temperature field of the high temperature rise combustion chamber have an important impact on the overall performance of the engine. However, the design and operation of the high temperature rise combustion chamber face many challenges, such as combustion stability, thermal protection, and emission control. The calculation of the gas temperature field is an important means to evaluate the performance of the combustion chamber, optimize the design, and improve the efficiency of the engine. By calculating the gas temperature field, we can understand the key parameters such as the temperature distribution, flow characteristics, and combustion efficiency of the gas in the combustion chamber, and provide a scientific basis for the improvement and optimization of the combustion chamber. At the same time, the calculation of the gas temperature field is also an important basis for evaluating the performance of the engine thermal protection system, predicting the engine life, and formulating maintenance plans. There is an urgent need for a calculation method for the gas temperature field. Summary of the invention

[0003] The purpose of the present invention is to provide a calculation method and acquisition device for the gas temperature field of an aircraft engine combustion chamber, so that the gas temperature field of the aircraft engine combustion chamber can be obtained, and key parameters such as the temperature distribution, flow characteristics and combustion efficiency of the gas in the combustion chamber can be understood.

[0004] In order to solve the above technical problems, an embodiment of the present invention provides a method for calculating the gas temperature field of an aircraft engine combustion chamber, comprising:

[0005] Obtain the combustion reaction equilibrium equation;

[0006] Calculate the residual gas coefficient α;

[0007] Calculate the oil-gas ratio f;

[0008] Calculate the combustion efficiency η;

[0009] Calculate the enthalpy value I of the combustion chamber outlet gas;

[0010] According to the calculated I value, the corresponding combustion temperature can be obtained using the enthalpy table.

[0011] In one embodiment, the combustion reaction equilibrium equation is:

[0012] CH a O b N c +XH2O+P0[R(O2)+S(N2)+T(CO2)+H2O]→CO2+H2O+O2+N2+CO+H2+CH4+NO+N

[0013] O2;

[0014] Among them, a, b, c are the molar ratios of H, O, N and C in the fuel; X is the molar ratio of the water injection volume in the combustion chamber to the fuel; P0 is the number of moles of air, and R, S, T are the volume fractions of O2, N2 and CO2 in the air.

[0015] In one embodiment, the residual gas coefficient α is calculated as follows:

[0016]

[0017] in,

[0018] In one embodiment, the oil-gas ratio f is calculated as follows:

[0019]

[0020] in,

[0021] In one embodiment, the combustion efficiency η is calculated as follows:

[0022]

[0023] Where: μg = 12.011 + 1.008a + 15.999b + 14.01c.

[0024] In one embodiment, the enthalpy value I of the combustion chamber outlet gas is calculated as: I×(1+f)=ia+f×(η×Hu+d°);

[0025] Among them, I is the enthalpy of the combustion chamber outlet gas; ia is the enthalpy of the combustion chamber inlet air; η is the combustion efficiency of the combustion chamber; Hu is the calorific value of the fuel; d° is the constant temperature combustion enthalpy difference of the fuel at 25°C.

[0026] In one embodiment, the constant temperature combustion enthalpy difference d° of the fuel at 25°C is as follows:

[0027]

[0028] in, is the formation enthalpy of CO2, is the formation enthalpy of H2O, and a is the molar ratio of H hydrogen to C carbon in the fuel.

[0029] An embodiment of the present invention provides a device for acquiring the combustion chamber gas temperature field of an aircraft engine, comprising: a sampling rake docked with the combustion chamber, a mass spectrometer docked with the sampling rake, and a controller electrically connected to the mass spectrometer, the sampling rake acquires the combustion chamber gas and transmits it to the mass spectrometer, the mass spectrometer analyzes the received combustion chamber gas to acquire its components, and the controller executes any one of the calculation methods described above according to the combustion chamber gas components analyzed by the mass spectrometer.

[0030] An embodiment of the present invention provides an electronic device, including:

[0031] A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the method for calculating the gas temperature field of an aircraft engine combustion chamber as described in any one of the above are implemented.

[0032] An embodiment of the present invention provides a computer-readable storage medium, on which an implementation program for information transmission is stored. When the program is executed by a processor, the steps of the method for calculating the gas temperature field of an aircraft engine combustion chamber as described in any one of the above are implemented.

[0033] Compared with the prior art, the embodiments of the present invention obtain the temperature field by calculating the combustion reaction equilibrium measurement results based on the components of the combustion chamber gas. Compared with the traditional thermocouple method, it has specific advantages in temperature measurement and can measure temperatures above 2000K with good independence, thereby obtaining the gas temperature field of the aircraft engine combustion chamber and understanding the key parameters such as the temperature distribution, flow characteristics and combustion efficiency of the gas in the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] One or more embodiments are exemplarily described by pictures in the corresponding drawings, and these exemplified descriptions do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings represent similar elements, and unless otherwise stated, the figures in the drawings do not constitute proportional limitations.

[0035] Figure 1 is a flow chart of a calculation method according to a first embodiment of the present invention. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical scheme and advantages of the embodiments of the present invention clearer, the following will be described in detail with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that in the various embodiments of the present invention, many technical details are provided in order to enable the reader to better understand the present application. However, even without these technical details and various changes and modifications based on the following embodiments, the technical scheme claimed in the present application can be implemented.

[0037] In the following description, certain specific details are set forth for the purpose of illustrating various disclosed embodiments to provide a thorough understanding of the various disclosed embodiments. However, those skilled in the relevant art will recognize that the embodiments may be practiced without one or more of these specific details. In other cases, well-known devices, structures, and techniques associated with the present application may not be shown or described in detail to avoid unnecessarily obscuring the description of the embodiments.

[0038] Unless the context requires otherwise, throughout the specification and claims, the word "comprise" and variations such as "include" and "have" should be construed in an open, inclusive sense, ie, should be interpreted as "including, but not limited to."

[0039] The following will be described in detail with reference to the accompanying drawings to provide a clearer understanding of the purpose, features and advantages of the present invention. It should be understood that the embodiments shown in the accompanying drawings are not intended to limit the scope of the present invention, but are only intended to illustrate the essential spirit of the technical solution of the present invention.

[0040] References throughout the specification to "one embodiment" or "an embodiment" indicate that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, the appearances of "in one embodiment" or "in an embodiment" in various places throughout the specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any manner in one or more embodiments.

[0041] As used in this specification and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. It should be noted that the term "or" is generally employed in its sense including "and / or" unless the context clearly dictates otherwise.

[0042] In the following description, in order to clearly show the structure and working mode of the present invention, many directional words will be used for description, but the words "front", "back", "left", "right", "outside", "inside", "outward", "inward", "up", "down", etc. should be understood as convenient terms and should not be understood as restrictive terms.

[0043] Embodiments of the present invention are described below with reference to the accompanying drawings.

[0044] The first embodiment of the present invention provides a method for calculating the combustion chamber gas temperature field of an aircraft engine. As a new combustion chamber testing technology, this method generally refers to a type of method for calculating the combustion chamber temperature field and component field based on the combustion chamber gas components. In response to the testing requirements of high thrust-to-mass ratio aircraft engine combustion chambers, this method combines the test results of a time-of-flight mass spectrometer, measures the combustion chamber component field by moving the combustion chamber sampling rake, and calculates the temperature field based on the component field measurement results. Compared with the traditional thermocouple method, it has specific advantages in temperature measurement: it can measure temperatures above 2000K and has good independence. The calculation method for the combustion chamber gas temperature field of an aircraft engine includes:

[0045] Obtain the combustion reaction equilibrium equation;

[0046] Calculate the residual gas coefficient α;

[0047] Calculate the oil-gas ratio f;

[0048] Calculate the combustion efficiency η;

[0049] Calculate the enthalpy value I of the combustion chamber outlet gas;

[0050] The outlet gas temperature T is obtained. Specifically, according to the calculated I value, the corresponding combustion temperature can be obtained using the enthalpy table.

[0051] Furthermore, the gas analysis technology measures the gas composition at the combustion chamber outlet, obtains the fuel-gas ratio of the combustion chamber through this method, and calculates the gas temperature by combining the inlet temperature of the combustion chamber, the gas enthalpy value and the average constant-pressure specific heat capacity.

[0052] The combustion reaction equilibrium equation is:

[0053] CH a O b N c +XH2O+P0[R(O2)+S(N2)+T(CO2)+H2O]→CO2+H2O+O2+N2+CO+H2+CH4+NO+N

[0054] O2;

[0055] Among them, a, b, c are the molar ratios of H, O, N and C in the fuel; X is the molar ratio of the water injection volume in the combustion chamber to the fuel; P0 is the number of moles of air, and R, S, T are the volume fractions of O2, N2 and CO2 in the air.

[0056] Furthermore, the residual gas coefficient α is calculated as follows:

[0057]

[0058] in,

[0059] Furthermore, the oil-gas ratio f is calculated as follows:

[0060]

[0061] in,

[0062] Furthermore, the combustion efficiency η is calculated as follows:

[0063]

[0064] Where: μg = 12.011 + 1.008a + 15.999b + 14.01c.

[0065] Furthermore, the enthalpy value I of the combustion chamber outlet gas is calculated as: I×(1+f)=ia+f×(η×Hu+d°);

[0066] Among them, I is the enthalpy of the combustion chamber outlet gas; ia is the enthalpy of the combustion chamber inlet air; η is the combustion efficiency of the combustion chamber; Hu is the calorific value of the fuel; d° is the constant temperature combustion enthalpy difference of the fuel at 25°C.

[0067] Specifically, enthalpy is an important state parameter that characterizes the energy of a material system in thermodynamics, which is equal to the sum of the internal energy and the product of pressure and volume. Enthalpy is a state function of the system and has nothing to do with the path of change. As long as the state of the system is determined, the enthalpy has a unique definite value. In the gas analysis method, the enthalpy of the gas is determined by the component concentration, temperature, pressure and volume flow rate. Given the pressure, volume, component concentration and gas enthalpy, the corresponding combustion temperature can be calculated, where I = I CO2 + I H2O + I O2 + I N2 + I CO + I H2 + I CH4 + I NO + I NO2.

[0068] Furthermore, the constant temperature combustion enthalpy difference d° of the fuel at 25°C is as follows:

[0069]

[0070] in, is the formation enthalpy of CO2, is the formation enthalpy of H2O, and a is the molar ratio of H hydrogen to C carbon in the fuel.

[0071] The second embodiment of the present invention provides a device for acquiring the combustion chamber gas temperature field of an aircraft engine, comprising: a sampling rake docked with the combustion chamber, a mass spectrometer docked with the sampling rake, and a controller electrically connected to the mass spectrometer, the sampling rake acquires the combustion chamber gas and transmits it to the mass spectrometer, the mass spectrometer analyzes the received combustion chamber gas to acquire its components, and the controller executes the calculation method described in the first embodiment above according to the combustion chamber gas components analyzed by the mass spectrometer.

[0072] The third embodiment of the present invention provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the steps of the method for calculating the gas temperature field of an aircraft engine combustion chamber as described in the first embodiment above.

[0073] The fourth embodiment of the present invention provides a computer-readable storage medium, on which a program for implementing information transmission is stored. When the program is executed by a processor, the steps of the method for calculating the gas temperature field of an aircraft engine combustion chamber as described in any one of the above are implemented.

[0074] Compared with the prior art, the embodiments of the present invention obtain the temperature field by calculating the combustion reaction equilibrium measurement results based on the components of the combustion chamber gas. Compared with the traditional thermocouple method, it has specific advantages in temperature measurement and can measure temperatures above 2000K with good independence, thereby obtaining the gas temperature field of the aircraft engine combustion chamber and understanding the key parameters such as the temperature distribution, flow characteristics and combustion efficiency of the gas in the combustion chamber.

[0075] It is not difficult to find that this embodiment is a system embodiment corresponding to the first embodiment, and this embodiment can be implemented in conjunction with the first embodiment. The relevant technical details mentioned in the first embodiment are still valid in this embodiment, and in order to reduce repetition, they are not repeated here. Accordingly, the relevant technical details mentioned in this embodiment can also be applied in the first embodiment.

[0076] Preferred embodiments of the present invention have been described above in detail, but it should be understood that aspects of the embodiments can be modified, if necessary, to employ aspects, features and concepts of the various patents, applications and publications to provide further embodiments.

[0077] These and other changes can be made to the embodiments in light of the above detailed description.In general, in the claims, the terms used should not be considered limited to the specific embodiments disclosed in the specification and the claims, but should be construed to include all possible embodiments along with the full scope of equivalents to which these claims are entitled.

[0078] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present invention, and in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present invention.

Claims

1. A method for calculating the gas temperature field of an aircraft engine combustion chamber, characterized in that: include: Obtain the combustion reaction equilibrium equation according to the composition of the combustion chamber gas; Calculate the residual gas coefficient α; Calculate the oil-gas ratio f; Calculate the combustion efficiency η; Calculate the enthalpy value I of the combustion chamber outlet gas; According to the calculated I value, the corresponding combustion temperature can be obtained using the enthalpy table.

2. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 1, characterized in that: The combustion reaction equilibrium equation is: CH a O b N c +XH2O+P0[R(O2)+S(N2)+T(CO2)+H2O]→CO2+H2O+O2+N2+CO+H2+CH4+NO+N O2； Among them, a, b, c are the molar ratios of H, O, N and C in the fuel; X is the molar ratio of the water injection volume in the combustion chamber to the fuel; P0 is the number of moles of air, and R, S, T are the volume fractions of O2, N2 and CO2 in the air.

3. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 2, characterized in that: The residual gas coefficient α is calculated as follows: in, 4. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 3, characterized in that: The oil-gas ratio f is calculated as follows: in, 5. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 4, characterized in that: The combustion efficiency η is calculated as follows: Where: μg = 12.011 + 1.008a + 15.999b + 14.01c.

6. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 5, characterized in that: The enthalpy value I of the combustion chamber outlet gas is calculated as: I×(1+f)=ia+f×(η×Hu+d°); Among them, I is the enthalpy of the combustion chamber outlet gas; ia is the enthalpy of the combustion chamber inlet air; η is the combustion efficiency of the combustion chamber; Hu is the calorific value of the fuel; d° is the constant temperature combustion enthalpy difference of the fuel at 25°C.

7. The calculation method for the combustion chamber gas temperature field of an aircraft engine according to claim 6, characterized in that: The constant temperature combustion enthalpy difference d° of the fuel at 25°C is as follows: in, is the formation enthalpy of CO2, is the formation enthalpy of H2O, and a is the molar ratio of H hydrogen to C carbon in the fuel.

8. A device for acquiring the gas temperature field of an aircraft engine combustion chamber, characterized in that: include: A sampling rake docked with the combustion chamber, a mass spectrometer docked with the sampling rake, and a controller electrically connected to the mass spectrometer, the sampling rake acquires combustion chamber gas and transmits it to the mass spectrometer, the mass spectrometer analyzes the received combustion chamber gas to acquire its components, and the controller executes the calculation method as claimed in any one of claims 1 to 7 according to the combustion chamber gas components analyzed by the mass spectrometer.

9. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the steps of a method for calculating the gas temperature field of an aircraft engine combustion chamber as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores an implementation program for information transmission, and when the program is executed by a processor, the steps of the method for calculating the gas temperature field of an aircraft engine combustion chamber as described in any one of claims 1 to 7 are implemented.

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