A method for calculating real-time gas temperature of a turbine disc cavity of an aero-engine
By using a one-dimensional calculation model and transient thermal balance equations, combined with an air system flow path model and parameter calibration, the accuracy and efficiency issues of real-time turbine disk cavity temperature calculation were solved, achieving efficient and accurate real-time calculation of turbine disk cavity temperature.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2023-03-01
- Publication Date
- 2026-05-19
AI Technical Summary
Existing technologies cannot accurately calculate turbine disk cavity temperature, especially during engine testing, where real-time calculations are not possible. Furthermore, traditional methods are inefficient or fail to account for the effects of solid heat capacity.
A one-dimensional calculation model combined with transient thermal balance equations is adopted. By acquiring the original test data and the air system flow path model, the modeled reference flow rate, intake temperature and heat transfer coefficient are calculated. Transient thermal balance calculation is performed by combining non-adjustable parameters, the turbine disk cavity air temperature is acquired in real time, and the calculation model is adjusted to meet the target requirements.
It achieves efficient real-time calculation of turbine disk cavity temperature, which can reflect the temperature difference during the engine's push-up and pull-down processes. The calculation is highly accurate and efficient, meeting the needs of real-time engine testing.
Smart Images
Figure CN116204983B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aero-engine technology, and specifically relates to a method for calculating the real-time temperature of the turbine disk cavity of an aero-engine. Background Technology
[0002] Turbine disks are a key component of aero-engines, and their transient temperatures significantly impact their strength, lifespan, and deformation. With aero-engines increasingly pursuing higher thrust-to-weight ratios and higher turbine inlet temperatures, the temperature margin of turbine disk components is being further compressed. This necessitates accurate and real-time analysis of turbine disk temperatures, supporting forward development activities such as structural and strength design within the design workflow, and providing technical support for safety assurance during test runs. The turbine disk cavity refers to the operating environment of the turbine disk, characterized by high-speed rotation, complex meridional vortex systems, and radial pressure-temperature stratification, resulting in complex flow and heat transfer. Typically, a turbine disk is surrounded by several cavities: the inlet cavity, the center cavity, and the outlet cavity. These three cavities together form the aerodynamic and thermodynamic environment of the high-speed rotating turbine disk. The real-time evolution and quantitative data of the gas temperature within these cavities are crucial factors determining the temperature evolution of turbine disk components. Accurate calculation of the turbine disk's transient temperature requires accurate turbine disk cavity air temperatures as boundary conditions.
[0003] In existing technologies, there are two methods for calculating turbine disk temperature: one is a one-dimensional calculation method based on empirical formulas, and the other is a three-dimensional fluid-structure interaction calculation method based on CFD calculation tools. The former mainly calculates based on steady-state conditions and does not consider the heat absorption and release processes of solid heat capacity. This means that it cannot accurately distinguish the temperature difference at the same converted speed during engine rise and fall, and therefore cannot obtain accurate gas temperature changes throughout the entire test process. The latter has better accuracy and richer field characteristic information, but its computational efficiency is too low to achieve the effect of real-time calculation during engine testing.
[0004] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Summary of the Invention
[0005] The purpose of this application is to provide a method for calculating the real-time temperature of the turbine disk cavity of an aero-engine, in order to solve at least one problem existing in the prior art.
[0006] The technical solution of this application is:
[0007] A method for calculating the real-time air temperature in the turbine disk cavity of an aero-engine, comprising:
[0008] Step 1: Obtain raw test data;
[0009] Step 2: Identify the air system flow path that affects the turbine disk cavity temperature, including the modeled reference flow rate calculation model, the modeled inlet air temperature calculation model, and the modeled heat transfer coefficient calculation model for the air system flow path;
[0010] Step 3: Obtain the non-adjustable parameters of the air system flow path;
[0011] Step 4: Using the original test data, the modeled baseline flow rate calculation model, the modeled intake air temperature calculation model, the modeled heat transfer coefficient calculation model, and the non-adjustable parameters as inputs, perform transient thermal balance calculations to obtain the real-time air temperature calculation results of the turbine disk cavity;
[0012] Step 5: Compare the real-time temperature calculation results with the test data. If the requirements are met, the calculation ends and the real-time temperature calculation results are output. If the requirements are not met, adjust the calculation models and return to Step 4.
[0013] In at least one embodiment of this application, the raw test data includes: compressor inlet total pressure P25, compressor inlet total temperature T25, physical speed N, converted speed nr, and physical time.
[0014] In at least one embodiment of this application, the air system flow path includes:
[0015] The first flow path has the bleed air position at the compressor outlet, which flows through the compressor outlet cavity to the turbine disk front cavity;
[0016] The second flow path has an intake gas location at the edge of the compressor intermediate stage disk, which flows through the disk core cavity to the rear cavity of the turbine disk.
[0017] In at least one embodiment of this application,
[0018] The model for calculating the baseline flow rate of the first flow path is as follows:
[0019] M1 = MC1 * m1 * P25 / T25 0.5 *nr
[0020] The model for calculating the baseline flow rate of the second flow path is as follows:
[0021] M2 = MC2 * m2 * P25 / T25 0.5 *nr
[0022] Where M1 is the modeled reference flow rate of the first flow path, MC1 is the flow rate adjustment coefficient of the first flow path, m1 is the reference flow rate of the first flow path, M2 is the modeled reference flow rate of the second flow path, MC2 is the flow rate adjustment coefficient of the second flow path, and m2 is the reference flow rate of the second flow path.
[0023] In at least one embodiment of this application,
[0024] The model for calculating the inlet temperature of the first flow path is as follows:
[0025] T1=(a1*nr 3 +b1*nr 2 +c1*nr+d1)*T25
[0026] The model for calculating the inlet temperature of the second flow path is as follows:
[0027] T2=(a2*nr 3 +b2*nr 2 +c2*nr+d2)*T25
[0028] Where T1 is the modeled inlet temperature of the first flow path, T2 is the modeled inlet temperature of the second flow path, and a1, b1, c1, d1, a2, b2, c2, and d2 are all constants obtained through polynomial fitting.
[0029] In at least one embodiment of this application,
[0030] The model for calculating the heat transfer coefficient of the first flow path is as follows:
[0031] H1 = HC1 * N 0.8
[0032] The model for calculating the heat transfer coefficient of the second flow path is as follows:
[0033] H2=HC2*N 0.8
[0034] Wherein, H1 is the modeled heat transfer coefficient of the first flow path, HC1 is the heat transfer coefficient adjustment coefficient of the first flow path, H2 is the modeled heat transfer coefficient of the second flow path, and HC2 is the heat transfer coefficient adjustment coefficient of the second flow path.
[0035] In at least one embodiment of this application, the non-adjustable parameter includes:
[0036] The heat exchange area A1 between the first flow path and the solid component, and the heat exchange area A2 between the second flow path and the solid component;
[0037] The specific heat capacity of the fluid in the first flow path is Cp_f1, and the specific heat capacity of the fluid in the second flow path is Cp_f2;
[0038] The density Rou, volume V, specific heat capacity Cp, and thermal conductivity λ of a solid.
[0039] In at least one embodiment of this application, in step five, if the index requirements are not met, the flow rate adjustment coefficients MC1 of the first flow path, MC2 of the second flow path, HC1 of the heat transfer coefficient of the first flow path, and HC2 of the heat transfer coefficient of the second flow path in the calculation model are adjusted.
[0040] The invention has at least the following beneficial technical effects:
[0041] The method for calculating the real-time temperature of the turbine disk cavity of an aero-engine disclosed in this application can realize the calculation of the real-time temperature of the turbine disk cavity of an aero-engine with high calculation efficiency. It solves the problem that traditional methods do not consider the coupling effect of solid heat absorption and release on temperature, or although they do consider it, the calculation efficiency is low. Attached Figure Description
[0042] Figure 1 This is a flowchart of a method for calculating the real-time air temperature of an aero-engine turbine disk cavity according to one embodiment of this application;
[0043] Figure 2 This is a schematic diagram of the airflow path of a turbine disk cavity air system according to one embodiment of this application. Detailed Implementation
[0044] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0045] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.
[0046] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.
[0047] This application provides a method for calculating the real-time air temperature of the turbine disk cavity in an aero-engine, such as... Figure 1 As shown, it includes the following steps:
[0048] Step 1: Obtain raw test data;
[0049] Step 2: Identify the air system flow path that affects the turbine disk cavity temperature, and calculate the simulated baseline flow rate, simulated inlet temperature, and simulated heat transfer coefficient of the air system flow path.
[0050] Step 3: Obtain the non-adjustable parameters of the air system flow path;
[0051] Step 4: Using the original test data, the modeled baseline flow rate calculation model, the modeled intake air temperature calculation model, the modeled heat transfer coefficient calculation model, and the non-adjustable parameters as input, perform transient thermal balance calculations to obtain the real-time air temperature calculation results of the turbine disk cavity.
[0052] Step 5: Compare the real-time temperature calculation results with the test data. If the requirements are met, the calculation ends and the real-time temperature calculation results are output. If the requirements are not met, adjust the calculation models and return to Step 4.
[0053] The method for calculating the real-time air temperature of the turbine disk cavity of the aero-engine in this application first extracts the compressor inlet total pressure P25, compressor inlet total temperature T25, physical speed N, converted speed nr, and physical time from the original engine test data.
[0054] Secondly, for the turbine disk cavity specifically requiring analysis, the air system flow paths affecting the cavity temperature are identified. Generally, two flow paths are selected. One flow path is the main inflow path into the cavity, and the other flow path is a relevant path that can alter the cavity temperature through thermal equilibrium. In this embodiment, as... Figure 2 As shown, the air system flow path includes a first flow path and a second flow path. The first flow path draws air from the compressor outlet, flowing through the compressor outlet cavity to the turbine disk front cavity. The second flow path draws air from the compressor intermediate stage disk rim, flowing through the disk center cavity to the turbine disk rear cavity. The first flow path is the main flow path, and the second flow path is a related flow path.
[0055] The method for calculating the real-time air temperature of the turbine disk cavity of an aero-engine in this application identifies the air system flow path and then determines the modeled reference flow calculation model, the modeled inlet air temperature calculation model, and the modeled heat transfer coefficient calculation model for the first and second flow paths.
[0056] In a preferred embodiment of this application,
[0057] The model for calculating the baseline flow rate of the first flow path is as follows:
[0058] M1 = MC1 * m1 * P25 / T25 0.5 *nr
[0059] The model for calculating the baseline flow rate of the second flow path is as follows:
[0060] M2 = MC2 * m2 * P25 / T25 0.5 *nr
[0061] Where M1 is the modeled reference flow rate of the first flow path, MC1 is the flow rate adjustment coefficient of the first flow path, m1 is the reference flow rate of the first flow path, M2 is the modeled reference flow rate of the second flow path, MC2 is the flow rate adjustment coefficient of the second flow path, and m2 is the reference flow rate of the second flow path.
[0062] MC1 and MC2 are the flow rate adjustment coefficients to be calibrated for the corresponding flow paths, and their values need to be determined based on test data; m1 and m2 are the reference flow rates for the corresponding flow paths, and their values can be given approximate orders of magnitude based on empirical values. By modeling the reference flow rate calculation model, the air system flow rate can be automatically adjusted according to different engine states.
[0063] In a preferred embodiment of this application,
[0064] The model for calculating the inlet temperature in the first flow path is as follows:
[0065] T1=(a1*nr 3 +b1*nr 2 +c1*nr+d1)*T25
[0066] The model for calculating the inlet temperature in the second flow path is as follows:
[0067] T2=(a2*nr 3 +b2*nr 2 +c2*nr+d2)*T25
[0068] Where T1 is the modeled inlet temperature of the first flow path, T2 is the modeled inlet temperature of the second flow path, and a1, b1, c1, d1, a2, b2, c2, and d2 are all constants obtained through polynomial fitting.
[0069] Based on engine test data, a1, b1, c1, d1, a2, b2, c2, and d2 are derived through polynomial fitting to formalize the intake air temperatures for the first and second flow paths. The independent variables in the modeled intake air temperature calculation are the converted engine speed nr and the compressor inlet total temperature T25. The calculated values of T1 and T2 need to be accurate to reflect the true intake air temperature. Inaccurate values will directly affect subsequent air temperature calculations and are difficult to correct through subsequent calibration. Therefore, the intake air temperature does not require subsequent calibration correction.
[0070] In a preferred embodiment of this application,
[0071] The model for calculating the heat transfer coefficient of the first flow path is as follows:
[0072] H1 = HC1 * N 0.8
[0073] The model for calculating the heat transfer coefficient of the second flow path is as follows:
[0074] H2=HC2*N 0.8
[0075] Wherein, H1 is the modeled heat transfer coefficient of the first flow path, HC1 is the heat transfer coefficient adjustment coefficient of the first flow path, H2 is the modeled heat transfer coefficient of the second flow path, and HC2 is the heat transfer coefficient adjustment coefficient of the second flow path.
[0076] The heat transfer coefficients between the two flow paths and the solid wall are calculated using a modeled heat transfer coefficient calculation method. HC1 and HC2 are the adjustment coefficients for the heat transfer coefficients to be calibrated, and their values need to be determined based on test data.
[0077] In transient thermal equilibrium calculations, certain non-adjustable parameters need to be input. In this embodiment, the non-adjustable parameters include:
[0078] The heat exchange area A1 between the first flow path and the solid component, and the heat exchange area A2 between the second flow path and the solid component;
[0079] The specific heat capacity of the fluid in the first flow path is Cp_f1, and the specific heat capacity of the fluid in the second flow path is Cp_f2;
[0080] The density Rou, volume V, specific heat capacity Cp, and thermal conductivity λ of a solid.
[0081] The method for calculating the real-time air temperature of the turbine disk cavity in this application involves obtaining various input parameters and a calculation model, and then performing transient thermal balance calculations based on the transient fluid-structure interaction thermal balance equation. Considering the influence of heat absorption and release by solid heat capacity, during engine thrust-up, the airflow temperature is relatively low after heat exchange with the turbine disk due to its lower temperature; conversely, during engine pull-down, the airflow temperature is relatively high after heat exchange with the turbine disk due to its higher temperature. This allows for the differentiation of air temperature differences at the same converted rotational speed during engine thrust-up and pull-down processes.
[0082] The method for calculating the real-time air temperature of the turbine disk cavity in this application obtains the calculation result through transient thermal balance calculation. The real-time air temperature calculation result of the main path (T) is then used. 流路一出口The data is compared with the test data to obtain the average deviation and maximum deviation over the entire process, and then compared with the calculated indicators. If the indicator requirements are met, the calculation ends; otherwise, the four calibration parameters MC1, MC2, HC1, and HC2 need to be further optimized until the indicator requirements are met. After meeting the indicator requirements, the calculated temperature result for this test run can be obtained. The calculation model constructed using the above four calibration parameters can be used to calculate the real-time temperature for other test runs, and can achieve high calculation accuracy.
[0083] The method for calculating the real-time air temperature of the turbine disk cavity in this application is based on a one-dimensional calculation model, but it no longer relies solely on empirical formulas. Instead, it improves the calculation accuracy by solving transient thermal balance equations and calibrating the calculation model against measured real-time data. Functionally, this application realizes the calculation of the real-time air temperature of the turbine disk cavity in aero-engines, reflecting the temperature differences during engine thrust-up and thrust-down processes. In terms of accuracy, it considers several factors affecting air temperature changes and adopts a modeling approach based on composite physical laws, thus ensuring calculation accuracy. In terms of efficiency, it has high calculation efficiency; the air temperature calculation time for 1 second of test run physical time is no more than 1 second, ensuring real-time calculation following the engine test process.
[0084] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A method for calculating the real-time air temperature of an aero-engine turbine disk cavity, characterized in that, include: Step 1: Obtain raw test data; Step 2: Identify the air system flow path that affects the turbine disk cavity temperature, including the modeled reference flow rate calculation model, the modeled inlet air temperature calculation model, and the modeled heat transfer coefficient calculation model for the air system flow path; Step 3: Obtain the non-adjustable parameters of the air system flow path; Step 4: Using the original test data, the modeled baseline flow rate calculation model, the modeled intake air temperature calculation model, the modeled heat transfer coefficient calculation model, and the non-adjustable parameters as inputs, perform transient thermal balance calculations to obtain the real-time air temperature calculation results of the turbine disk cavity; Step 5: Compare the real-time temperature calculation results with the test data. If the index requirements are met, the calculation ends and the real-time temperature calculation results are output. If the requirements are not met, adjust the various calculation models and return to step four. The original test data includes: compressor inlet total pressure P25, compressor inlet total temperature T25, physical speed N, converted speed nr, and physical time. The air system flow path includes: The first flow path has the bleed air position at the compressor outlet, which flows through the compressor outlet cavity to the turbine disk front cavity; The second flow path has an intake air location at the edge of the intermediate stage disk of the compressor, which flows through the disk core cavity to the rear cavity of the turbine disk; The model for calculating the baseline flow rate of the first flow path is as follows: M1=MC1*m1*P25 / T25 0.5 *nr; The model for calculating the baseline flow rate of the second flow path is as follows: M2 = MC2 * m2 * P25 / T25 0.5 *nr; Where M1 is the modeled reference flow rate of the first flow path, MC1 is the flow rate adjustment coefficient of the first flow path, m1 is the reference flow rate of the first flow path, M2 is the modeled reference flow rate of the second flow path, MC2 is the flow rate adjustment coefficient of the second flow path, and m2 is the reference flow rate of the second flow path.
2. The method for calculating the real-time air temperature of the turbine disk cavity of an aero-engine according to claim 1, characterized in that, The model for calculating the inlet temperature of the first flow path is as follows: T1=(a1*nr) 3 +b1*no 2 +c1*nr+d1)*T25; The model for calculating the inlet temperature of the second flow path is as follows: T2 = (a2*nr) 3 +b2*nr 2 +c2*nr+d2)*T25; Where T1 is the modeled inlet temperature of the first flow path, T2 is the modeled inlet temperature of the second flow path, and a1, b1, c1, d1, a2, b2, c2, and d2 are all constants obtained through polynomial fitting.
3. The method for calculating the real-time air temperature of the turbine disk cavity of an aero-engine according to claim 2, characterized in that, The model for calculating the heat transfer coefficient of the first flow path is as follows: H1=HC1*N 0.8 ; The model for calculating the heat transfer coefficient of the second flow path is as follows: H2=HC2*N 0.8 ; Wherein, H1 is the modeled heat transfer coefficient of the first flow path, HC1 is the heat transfer coefficient adjustment coefficient of the first flow path, H2 is the modeled heat transfer coefficient of the second flow path, and HC2 is the heat transfer coefficient adjustment coefficient of the second flow path.
4. The method for calculating the real-time air temperature of the turbine disk cavity of an aero-engine according to claim 3, characterized in that, In step five, if the target requirements are not met, the flow rate adjustment coefficients MC1 for the first flow path, MC2 for the second flow path, HC1 for the first flow path, and HC2 for the second flow path in the calculation model are adjusted.