Power turbine disk stress cycle calculation and engine life management method, system

Abstract

The application relates to the technical field of aviation turbine shaft engines, and discloses a power turbine disc stress cycle calculation and engine life management method and system, which comprises the following steps: acquiring the power turbine rotor rotating speed and the gas turbine outlet temperature and converting the acquired data into regular cycle data to extract the pulsating stress cycle data; calculating the stress of key positions of the power turbine rotor at the rated rotating speed according to the pulsating stress cycle data of the power turbine rotor rotating speed, and calculating the stress caused by the temperature field of the key positions of the power turbine rotor at different rotating speeds except the rated rotating speed in combination with the pulsating stress cycle data of the power turbine rotor rotating speed and the gas turbine outlet temperature; calculating the centrifugal stress and the temperature stress of the power turbine rotor at the maximum rotating speed and obtaining the resultant stress from the centrifugal stress and the temperature stress; and calculating the maximum equivalent stress according to the resultant stress and performing life management. The application can ensure the stress calculation precision of the power turbine disc, improve the calculation efficiency, and prolong the service life of the aviation turbine shaft engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero turbine shaft engine, in particular to a power turbine disc stress cycle calculation and engine life management method and system. BACKGROUND

[0002] Real-time calculation of fatigue damage (FD) of key parts of an aero turbine shaft engine can timely obtain the health status of the engine to realize life management of the aero turbine shaft engine, thereby prolonging the service life of the engine and improving the safety and reliability of the engine and the aircraft.

[0003] The calculation of fatigue damage can be realized by calculating the stress cycle of the power turbine disc, as shown in the following formula: Figure 1 The stress distribution diagram of the aero turbine shaft engine during operation is shown in the following figure, Figure 1 The "maximum stress position" on the power turbine disc is the key position of fatigue damage. In the prior art, the life management system of the aero turbine shaft engine usually includes a ground system and an on-board system arranged on the aircraft. The on-board system obtains the real-time stress cycle and temperature data of each part (the structure of the turbine shaft engine is shown in the following figure, including axial compressor, centrifugal compressor, combustion chamber, gas turbine, power turbine, etc.) during operation of the turbine shaft engine through a collection system (for example, a health and usage monitoring system) and transmits them to the ground system. The ground system calculates the stress cycle of the power turbine disc according to the real-time stress cycle and temperature data to calculate the fatigue damage of the key position of the engine. Figure 2

[0004] However, in the calculation of the stress cycle of the power turbine disc, the existing calculation method often cannot effectively extract key data, and in order to ensure the calculation accuracy, it is necessary to calculate according to all the collected real-time stress and temperature data, which has large calculation amount and low efficiency. SUMMARY

[0005] Therefore, the technical problem to be solved by the present application is to overcome the deficiencies in the prior art and provide a power turbine disc stress cycle calculation and engine life management method and system, which can effectively extract key data, improve the calculation efficiency while ensuring the calculation accuracy of the stress of the power turbine disc, and based on this, calculate the fatigue damage and manage the life of the engine, thereby effectively prolonging the service life of the aero turbine shaft engine.

[0006] To solve the above technical problems, the present application provides a power turbine disc stress cycle calculation method, comprising:

[0007] ​The power turbine rotor speed data and the gas turbine outlet temperature data during the operation of the aero turbine shaft engine are acquired, the irregular power turbine rotor speed data and the gas turbine outlet temperature data are converted into regular power turbine rotor speed cycle data and gas turbine outlet temperature cycle data using a cycle counting method, and pulsating stress cycle data in the cycle data are extracted;

[0008] The stress of the key position of the power turbine rotor at the rated speed is calculated according to the pulsating stress cycle data of the power turbine rotor speed, and the stress of the key position of the power turbine rotor at different speeds except the rated speed is calculated according to the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature.

[0009] The centrifugal stress of the power turbine rotor at the maximum speed is calculated according to the stress of the key position of the power turbine rotor at the rated speed, the temperature stress of the power turbine rotor at the maximum speed is calculated according to the stress of the key position of the power turbine rotor at different speeds except the rated speed, the combined stress of the power turbine rotor at the maximum speed is obtained by combining the centrifugal stress of the power turbine rotor at the maximum speed and the temperature stress of the power turbine rotor at the maximum speed.

[0010] The maximum equivalent stress of the power turbine rotor is obtained according to the multiple components of the combined stress of the power turbine rotor at the maximum speed based on the calculation method of the equivalent stress.

[0011] Further, the stress of the key position of the power turbine rotor at the rated speed is calculated according to the pulsating stress cycle data of the power turbine rotor speed, and the stress of the key position of the power turbine rotor at the rated speed is calculated using a finite element simulation method according to the multiple stress components of the power turbine rotor at the rated speed.

[0012] The stress of the key position of the power turbine rotor at different speeds except the rated speed is calculated according to the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature, and the multiple stress components of the key position of the power turbine rotor at two different speeds except the rated speed are calculated using a finite element simulation method according to the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature.

[0013] Further, the stress of the key position of the power turbine rotor at the rated speed includes six stress components, and the stress of the key position of the power turbine rotor at the rated speed is specifically:

[0014] ,

[0015] wherein, is the stress of the key position of the power turbine rotor at the rated speed, represents the component of the stress of the key position of the power turbine rotor at the rated speed, ij=11 represents the X-axis directional stress in the X-direction plane, ij=22 represents the Y-axis directional stress in the Y-direction plane, ij=33 represents the Z-axis directional stress in the Z-direction plane, ij=12 represents the Y-axis directional stress in the X-direction plane, ij=23 represents the Z-axis directional stress in the Y-direction plane, and ij=31 represents the X-axis directional stress in the Z-direction plane.

[0016] Further, the stress of the key position of the power turbine rotor at two different speeds other than the rated speed caused by the temperature field comprises six stress components, denoted as a first speed and a second speed, wherein the first speed is greater than the second speed; denoted as the stress of the key position of the power turbine rotor at the first speed caused by the temperature field, , and the stress of the key position of the power turbine rotor at the second speed caused by the temperature field, , and Specifically,

[0017] ,

[0018] ;

[0019] wherein, represents the component of the stress of the key position of the power turbine rotor at the first speed caused by the temperature field, represents the component of the stress of the key position of the power turbine rotor at the second speed caused by the temperature field, ij=11 represents the X-axis directional stress in the X-direction plane, ij=22 represents the Y-axis directional stress in the Y-direction plane, ij=33 represents the Z-axis directional stress in the Z-direction plane, ij=12 represents the Y-axis directional stress in the X-direction plane, ij=23 represents the Z-axis directional stress in the Y-direction plane, and ij=31 represents the X-axis directional stress in the Z-direction plane.

[0020] Further, the centrifugal stress of the power turbine rotor at the maximum speed is calculated according to the stress of the key position of the power turbine rotor at the rated speed, specifically:

[0021] The component of the centrifugal stress of the power turbine rotor at the maximum speed is calculated according to the component of the stress of the key position of the power turbine rotor at the rated speed, specifically:

[0022] ,

[0023] wherein, represents a component of the centrifugal stress of the power turbine rotor at the maximum rotational speed, N represents the maximum rotational speed, and NP represents the rated rotational speed;

[0024] The centrifugal stress of the power turbine rotor at the maximum rotational speed is obtained as follows:

[0025] ,

[0026] wherein, is the centrifugal stress of the power turbine rotor at the maximum rotational speed.

[0027] Further, the calculation method of the temperature stress of the power turbine rotor at the maximum rotational speed is as follows:

[0028] ,

[0029] wherein, represents the temperature stress of the power turbine rotor at the maximum rotational speed, is the maximum rotational speed, is the first rotational speed, is the second rotational speed.

[0030] Further, according to the plurality of components of the combined stress of the power turbine rotor at the maximum rotational speed, the maximum equivalent stress of the power turbine rotor is obtained based on the calculation method of the equivalent stress, specifically as follows:

[0031] The maximum equivalent stress of the power turbine rotor is calculated according to the six components of the combined stress of the power turbine rotor at the maximum rotational speed as follows:

[0032] ,

[0033] wherein, is the maximum equivalent stress of the power turbine rotor, and k1 and k2 are adjustment weights, represents the X-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the X-direction plane, represents the Y-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the Y-direction plane, represents the Z-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the Z-direction plane, represents the Y-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the X-direction plane, represents the Z-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the Y-direction plane, represents the X-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the Z-direction plane.

[0034] The application also provides a power turbine disc stress cycle calculation system, comprising:

[0035] a data acquisition module, configured to acquire power turbine rotor speed data and gas turbine outlet temperature data when the aero turbine shaft engine is working;

[0036] a data extraction module, configured to convert irregular power turbine rotor speed data and gas turbine outlet temperature data into regular power turbine rotor speed cycle data and gas turbine outlet temperature cycle data by using a cycle counting method, and extract pulsating stress cycle data in the cycle data;

[0037] a key position stress calculation module, configured to calculate the stress of a key position of the power turbine rotor at a rated speed according to the pulsating stress cycle data of the power turbine rotor speed, and calculate the stress of the key position of the power turbine rotor at different speeds except the rated speed caused by a temperature field according to the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature;

[0038] a combined stress calculation module, configured to calculate the centrifugal stress of the power turbine rotor at a maximum speed according to the stress of the key position of the power turbine rotor at the rated speed, calculate the temperature stress of the power turbine rotor at the maximum speed according to the stress of the key position of the power turbine rotor at different speeds except the rated speed caused by the temperature field, and obtain the combined stress of the power turbine rotor at the maximum speed by combining the centrifugal stress of the power turbine rotor at the maximum speed and the temperature stress of the power turbine rotor at the maximum speed;

[0039] a maximum equivalent stress calculation module, configured to obtain the maximum equivalent stress of the power turbine rotor according to a plurality of components of the combined stress of the power turbine rotor at the maximum speed based on a calculation method of equivalent stress.

[0040] The application also provides an engine life management method, which uses the power turbine disc stress cycle calculation method to calculate the maximum equivalent stress of the power turbine rotor in real time when the aero turbine shaft engine is working, calculates the real-time fatigue damage of a key position of the aero turbine shaft engine according to the maximum equivalent stress of the power turbine rotor, adjusts the working state of the aero turbine shaft engine according to the real-time fatigue damage, and realizes the life management of the aero turbine shaft engine.

[0041] The application also provides an engine life management system, comprising:

[0042] a data acquisition module, configured to acquire power turbine rotor speed data and gas turbine outlet temperature data when the aero turbine shaft engine is working;

[0043] a data extraction module configured to convert irregular power turbine rotor speed data and gas turbine outlet temperature data into regular cycle data of power turbine rotor speed and cycle data of gas turbine outlet temperature using a cycle counting method, and extract pulsating stress cycle data from the cycle data;

[0044] a critical site stress calculation module configured to calculate stress of a critical site of the power turbine rotor at a rated speed according to the pulsating stress cycle data of the power turbine rotor speed, and calculate stress of the critical site of the power turbine rotor at different speeds other than the rated speed according to the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature;

[0045] a combined stress calculation module configured to calculate centrifugal stress of the power turbine rotor at a maximum speed according to the stress of the critical site of the power turbine rotor at the rated speed, calculate temperature stress of the power turbine rotor at the maximum speed according to the stress of the critical site of the power turbine rotor at different speeds other than the rated speed, and obtain combined stress of the power turbine rotor at the maximum speed according to the centrifugal stress of the power turbine rotor at the maximum speed and the temperature stress of the power turbine rotor at the maximum speed;

[0046] a maximum equivalent stress calculation module configured to obtain maximum equivalent stress of the power turbine rotor according to a plurality of components of the combined stress of the power turbine rotor at the maximum speed based on a calculation method of equivalent stress;

[0047] a life management module configured to calculate real-time fatigue damage of the critical site of the aero turbine shaft engine according to the maximum equivalent stress of the power turbine rotor, adjust a working state of the aero turbine shaft engine according to the real-time fatigue damage, and realize life management of the aero turbine shaft engine.

[0048] The above technical solution of the present application has the following beneficial effects compared with the prior art:

[0049] The present application converts irregular power turbine rotor speed data and gas turbine outlet temperature data into regular cycle data of power turbine rotor speed and cycle data of gas turbine outlet temperature, extracts pulsating stress cycle data from the cycle data, and uses the pulsating stress cycle data for subsequent maximum equivalent stress calculation, thereby realizing effective extraction of critical data, improving calculation efficiency while ensuring the calculation accuracy of power turbine disc stress, and prolonging the service life of the aero turbine shaft engine based on fatigue damage calculation according to the calculated maximum equivalent stress for life management of the aero turbine shaft engine. BRIEF DESCRIPTION OF DRAWINGS

[0050] In order to make the content of the present application more easily understood, the present application is further described in detail below according to specific embodiments of the present application and in conjunction with the accompanying drawings, in which:

[0051] Figure 1 A schematic diagram of stress distribution during operation of an aero turbine shaft engine.

[0052] Figure 2 A schematic diagram of the structure of a turbine shaft engine.

[0053] Figure 3 A flow chart of the stress cycle calculation method for a power turbine disk in a preferred embodiment of the present application.

[0054] Figure 4 A curve diagram example of the power turbine rotor speed, the gas turbine rotor speed, and the temperature index during operation of an aero turbine shaft engine.

[0055] Figure 5 A schematic diagram of stress cycle.

[0056] Figure 6 A schematic diagram of pulsating stress cycle. DETAILED DESCRIPTION

[0057] The present application is further described below in conjunction with the accompanying drawings and specific embodiments so that those skilled in the art can better understand the present application and implement it, but the embodiments are not intended to limit the present application.

[0058] Referring to Figure 3 The present application discloses a stress cycle calculation method for a power turbine disk, comprising the following steps:

[0059] S1: Obtain the power turbine rotor speed data and the gas turbine outlet temperature data during operation of an aero turbine shaft engine, and convert the irregular power turbine rotor speed data and the gas turbine outlet temperature data into regular power turbine rotor speed cycle data and gas turbine outlet temperature cycle data using a cycle counting method, wherein the cycle data comprises pulsating stress cycle data (i.e. primary cycle) and stress cycle data (i.e. secondary cycle), and the pulsating stress cycle data (i.e. primary cycle) is used in the present application.

[0060] The maximum stress of a turbine disk is mainly determined by the speed (about 80%), followed by the temperature. Figure 4 A curve diagram example of the power turbine rotor speed (NP), the gas turbine rotor speed (NG), and the gas turbine outlet temperature (T45) during operation of an aero turbine shaft engine, Figure 4 The horizontal coordinate is time. For the power turbine rotor speed and the gas turbine rotor speed, the vertical coordinate is percentage, and the rated speed is 100%; for the gas turbine outlet temperature, the vertical coordinate is temperature x 10℃. From the curve diagram, it can be seen that the power turbine rotor speed and the gas turbine rotor speed are not constant, but change with time, and the gas turbine outlet temperature also changes with time.Figure 4 It can be seen that the fluctuation range of the power turbine rotor speed is significantly smaller than the fluctuation range of the gas turbine rotor speed and the fluctuation range of the gas turbine outlet temperature.

[0061] As shown in Figure 5 is a schematic diagram of stress cycles, the process of stress from minimum to maximum and back to minimum is a stress cycle. As shown in Figure 6 is a pulsating stress cycle, the process of stress from 0 to maximum and back to 0 is a pulsating stress cycle. The fatigue damage of a part is calculated for each different stress cycle, and then the total damage is obtained by damage accumulation (using the Miner rule, etc.). The larger the range of the cycle (the difference between the maximum and minimum), the greater the fatigue damage.

[0062] The calculation of fatigue damage can be achieved by calculating the stress cycle of the power turbine disc, so in the present application, the stress of the power turbine disc is calculated by combining the power turbine rotor speed and the gas turbine outlet temperature. The irregular power turbine rotor speed and the gas turbine outlet temperature cycle shown in Figure 4 are converted into a series of regular cycle data as shown in Figure 5 , Figure 6 .

[0063] The function of the aircraft engine life management system is to calculate the fatigue damage of the key parts for each flight, so as to understand the use state of the important parts. The aircraft engine parts experience two types of cycles:

[0064] The first type is the main cycle, that is, the "0 to maximum to 0" pulsating stress cycle as shown in Figure 6 , that is, the "0" state before takeoff to the maximum value during flight, and finally to the "0" state after landing and stopping.

[0065] The second type is the secondary cycle, that is, the stress cycle as shown in Figure 5 It can be seen from Figure 4 that the gas turbine rotor speed and temperature both have many small secondary cycles, and the secondary cycle of the power turbine rotor speed is very small. All the secondary cycles need to be considered in the current calculation method, so the calculation amount is large. Because the secondary cycle of the power turbine rotor speed is very small, the fatigue damage generated can be ignored, so in the damage calculation of the present application, the secondary cycle of the power turbine rotor speed is ignored and only the damage caused by the main cycle is considered, thereby greatly simplifying the calculation.

[0066] As can be seen from Figure 2 , the position of the gas turbine outlet is in front of the power turbine, and the temperature is transferred from the blade to the disc, especially to Figure 1The fluctuation range (cycle range) of the maximum stress is significantly reduced. In addition, the influence of temperature on the maximum stress of the wheel disc is much smaller than that of the rotating speed, so the fatigue damage caused by temperature secondary cycles can be ignored. After this treatment, the temperature and the rotating speed experience the pulsating stress cycle of "0 to maximum to 0" synchronously. Since the minimum value of the main cycle is 0, no additional calculation is required, so only the maximum value is calculated in the present application.

[0067] S2: Calculate the stress of the key position of the power turbine rotor at the rated rotating speed according to the pulsating stress cycle data of the power turbine rotor rotating speed.

[0068] According to the pulsating stress cycle data of the power turbine rotor rotating speed, the six stress components of the key position of the power turbine rotor at the rated rotating speed are calculated using the finite element simulation method (such as using ANSYS software for finite element simulation), and the stress of the key position of the power turbine rotor at the rated rotating speed is obtained as follows:

[0069] ,

[0070] wherein, is the stress of the key position of the power turbine rotor at the rated rotating speed, represents the component of the stress of the key position of the power turbine rotor at the rated rotating speed, ij=11 represents the X-axis stress in the X-direction plane, ij=22 represents the Y-axis stress in the Y-direction plane, ij=33 represents the Z-axis stress in the Z-direction plane, ij=12 represents the Y-axis stress in the X-direction plane, ij=23 represents the Z-axis stress in the Y-direction plane, and ij=31 represents the X-axis stress in the Z-direction plane.

[0071] In this embodiment, the rated rotating speed is 100%, and the six stress components of the key position of the power turbine rotor at the rated rotating speed are calculated as follows: which can also be expressed as:

[0072] ,

[0073] wherein, represents the stress of the key position of the power turbine rotor at the rotating speed of 100%, represents the X-axis stress in the X-direction plane of the key position of the power turbine rotor at the rotating speed of 100%, represents the Y-axis stress in the Y-direction plane of the key position of the power turbine rotor at the rotating speed of 100%, represents the Z-axis stress in the Z-direction plane of the key position of the power turbine rotor at the rotating speed of 100%, represents the Y-axis stress in the X-direction plane of the key position of the power turbine rotor at the rotating speed of 100%, represents the Z axial stress of the key position of the power turbine rotor in the Y direction plane at the rotational speed of 100%, and represents the X axial stress of the key position of the power turbine rotor in the Z direction plane at the rotational speed of 100%.

[0074] S3: combining the fluctuating stress cycle data of the rotational speed of the power turbine rotor and the fluctuating stress cycle data of the gas turbine outlet temperature, calculating the stress caused by the temperature field of the key position of the power turbine rotor at different rotational speeds except the rated rotational speed by using the finite element simulation method.

[0075] Combining the fluctuating stress cycle data of the rotational speed of the power turbine rotor and the fluctuating stress cycle data of the gas turbine outlet temperature, calculating the stress caused by the temperature field of the key position of the power turbine rotor at two different rotational speeds except the rated rotational speed by using the finite element simulation method, obtaining the stress caused by the temperature field of the key position of the power turbine rotor at two different rotational speeds except the rated rotational speed; the two different rotational speeds are respectively a first rotational speed and a second rotational speed, and the first rotational speed is greater than the second rotational speed; the stress caused by the temperature field of the key position of the power turbine rotor at the first rotational speed is , and the stress caused by the temperature field of the key position of the power turbine rotor at the second rotational speed is , and Specifically:

[0076] ,

[0077] ;

[0078] wherein, represents the component of the stress caused by the temperature field of the key position of the power turbine rotor at the first rotational speed, represents the component of the stress caused by the temperature field of the key position of the power turbine rotor at the second rotational speed, ij=11 represents the X axial stress in the X direction plane, ij=22 represents the Y axial stress in the Y direction plane, ij=33 represents the Z axial stress in the Z direction plane, ij=12 represents the Y axial stress in the X direction plane, ij=23 represents the Z axial stress in the Y direction plane, and ij=31 represents the X axial stress in the Z direction plane.

[0079] The first rotational speed and the second rotational speed can be adjusted according to actual conditions. In the embodiment, the first rotational speed is 102% of the rated rotational speed, and the second rotational speed is 99% of the rated rotational speed. The six stress components caused by the temperature field of the key position of the power turbine rotor at two different rotational speeds except the rated rotational speed are calculated, that is, which can also be expressed as:

[0080] ,

[0081] wherein, represents the stress caused by the temperature field of the critical location when the power turbine rotor speed is 102% of the rated speed, represents the X-axis directional stress of the temperature field of the critical location in the X-direction plane when the power turbine rotor speed is 102% of the rated speed, represents the Y-axis directional stress of the temperature field of the critical location in the Y-direction plane when the power turbine rotor speed is 102% of the rated speed, represents the Z-axis directional stress of the temperature field of the critical location in the Z-direction plane when the power turbine rotor speed is 102% of the rated speed, represents the Y-axis directional stress of the temperature field of the critical location in the X-direction plane when the power turbine rotor speed is 102% of the rated speed, represents the Z-axis directional stress of the temperature field of the critical location in the Y-direction plane when the power turbine rotor speed is 102% of the rated speed, represents the X-axis directional stress of the temperature field of the critical location in the Z-direction plane when the power turbine rotor speed is 102% of the rated speed.

[0082] may also be represented as:

[0083] ,

[0084] wherein, represents the stress caused by the temperature field of the critical location when the power turbine rotor speed is 99% of the rated speed, represents the X-axis directional stress of the temperature field of the critical location in the X-direction plane when the power turbine rotor speed is 99% of the rated speed, represents the Y-axis directional stress of the temperature field of the critical location in the Y-direction plane when the power turbine rotor speed is 99% of the rated speed, represents the Z-axis directional stress of the temperature field of the critical location in the Z-direction plane when the power turbine rotor speed is 99% of the rated speed, represents the Y-axis directional stress of the temperature field of the critical location in the X-direction plane when the power turbine rotor speed is 99% of the rated speed, represents the Z-axis directional stress of the temperature field of the critical location in the Y-direction plane when the power turbine rotor speed is 99% of the rated speed, represents the X-axis directional stress of the temperature field of the critical location in the Z-direction plane when the power turbine rotor speed is 99% of the rated speed.

[0085] S4: calculating the centrifugal stress of the power turbine rotor at the maximum speed according to the stress of the critical location of the power turbine rotor at the rated speed.

[0086] S4-1: the component of the centrifugal stress of the power turbine rotor at the maximum rotating speed is calculated according to the component of the stress of the key position of the power turbine rotor at the rated rotating speed, as follows:

[0087] ,

[0088] wherein, represents the component of the centrifugal stress of the power turbine rotor at the maximum rotating speed, represents the component of the stress of the key position of the power turbine rotor at the rated rotating speed, N represents the maximum rotating speed, and NP represents the rated rotating speed;

[0089] In this embodiment, six components of the centrifugal stress of the power turbine rotor at the maximum rotating speed are calculated, as follows:

[0090] ,

[0091] ,

[0092] ,

[0093] ,

[0094] ,

[0095] ;

[0096] wherein, represents the X-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the X-direction plane, represents the Y-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the Y-direction plane, represents the Z-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the Z-direction plane, represents the Y-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the X-direction plane, represents the Z-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the Y-direction plane, represents the X-axis directional stress of the centrifugal stress of the power turbine rotor at the maximum rotating speed in the Z-direction plane.

[0097] S4-2: the centrifugal stress of the power turbine rotor at the maximum rotating speed is obtained as follows:

[0098] ,

[0099] wherein, is the centrifugal stress of the power turbine rotor at the maximum rotating speed, and can also be expressed as:

[0100] .

[0101] S5: calculating the temperature stress of the power turbine rotor at the maximum rotational speed in combination with the stress caused by the temperature field of the key parts of the power turbine rotor at different rotational speeds other than the rated rotational speed.

[0102] The first rotational speed is greater than the second rotational speed, and the method for calculating the temperature stress of the power turbine rotor at the maximum rotational speed is:

[0103] ,

[0104] wherein, represents the temperature stress of the power turbine rotor at the maximum rotational speed, is the maximum rotational speed, is the first rotational speed, is the second rotational speed.

[0105] In the embodiment, the first rotational speed is 102% of the rated rotational speed, and the second rotational speed is 99% of the rated rotational speed, i.e. .

[0106] S6: obtaining the combined stress of the power turbine rotor at the maximum rotational speed in combination with the centrifugal stress of the power turbine rotor at the maximum rotational speed and the temperature stress of the power turbine rotor at the maximum rotational speed, which is:

[0107] ,

[0108] wherein, is the combined stress of the power turbine rotor at the maximum rotational speed, and correspondingly, there are also 6 components, i.e. which can be expressed as:

[0109] .

[0110] S7: obtaining the maximum equivalent stress of the power turbine rotor based on the calculation method of the equivalent stress according to the multiple components of the combined stress of the power turbine rotor at the maximum rotational speed.

[0111] The maximum equivalent stress of the power turbine rotor is calculated according to the 6 components of the combined stress of the power turbine rotor at the maximum rotational speed, which is:

[0112] ,

[0113] wherein, is the maximum equivalent stress of the power turbine rotor, and k1 and k2 are adjustment weights, represents the X-axis directional stress of the combined stress of the power turbine rotor at the maximum rotational speed in the X-direction plane, represents Y axial stress of the resultant stress of the power turbine rotor at the maximum rotational speed on the Y direction plane, represents Z axial stress of the resultant stress of the power turbine rotor at the maximum rotational speed on the Z direction plane, represents Y axial stress of the resultant stress of the power turbine rotor at the maximum rotational speed on the X direction plane, represents Z axial stress of the resultant stress of the power turbine rotor at the maximum rotational speed on the Y direction plane, represents X axial stress of the resultant stress of the power turbine rotor at the maximum rotational speed on the Z direction plane, the values of k1 and k2 can be adjusted according to actual conditions, and in the embodiment, k1=0.5 and k2=3.

[0114] The application further discloses a power turbine disk stress cycle calculation system, comprising:

[0115] a data acquisition module, configured to acquire power turbine rotor rotational speed data and gas turbine outlet temperature data when the aero turbine shaft engine is working;

[0116] a data extraction module, configured to convert irregular power turbine rotor rotational speed data and gas turbine outlet temperature data into regular power turbine rotor rotational speed cycle data and gas turbine outlet temperature cycle data by using a cycle counting method, and extract pulsating stress cycle data in the cycle data;

[0117] a key position stress calculation module, configured to calculate stress of a key position of the power turbine rotor at a rated rotational speed according to the pulsating stress cycle data of the power turbine rotor rotational speed, and calculate stress of the key position caused by a temperature field of the power turbine rotor at different rotational speeds except the rated rotational speed according to the pulsating stress cycle data of the power turbine rotor rotational speed and the pulsating stress cycle data of the gas turbine outlet temperature;

[0118] a resultant stress calculation module, configured to calculate centrifugal stress of the power turbine rotor at the maximum rotational speed according to the stress of the key position of the power turbine rotor at the rated rotational speed, calculate temperature stress of the power turbine rotor at the maximum rotational speed according to the stress of the key position caused by the temperature field of the power turbine rotor at different rotational speeds except the rated rotational speed, and obtain resultant stress of the power turbine rotor at the maximum rotational speed according to the centrifugal stress of the power turbine rotor at the maximum rotational speed and the temperature stress of the power turbine rotor at the maximum rotational speed;

[0119] a maximum equivalent stress calculation module, configured to obtain maximum equivalent stress of the power turbine rotor according to multiple components of the resultant stress of the power turbine rotor at the maximum rotational speed and based on a calculation method of equivalent stress.

[0120] The application further discloses an engine life management method, which uses the power turbine disc stress cycle calculation method to calculate the maximum equivalent stress of a power turbine rotor of an aero turbine shaft engine in real time, calculates real-time fatigue damage of a key position of the aero turbine shaft engine according to the maximum equivalent stress of the power turbine rotor, adjusts the working state of the aero turbine shaft engine according to the real-time fatigue damage, and realizes life management of the aero turbine shaft engine.

[0121] The application further discloses an engine life management system, which comprises a life management module in addition to various modules in the power turbine disc stress cycle calculation system.

[0122] The application further discloses a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to realize the power turbine disc stress cycle calculation method or the engine life management method.

[0123] The application further discloses an apparatus comprising a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor realizes the power turbine disc stress cycle calculation method or the engine life management method when executing the computer program.

[0124] The application realizes effective screening of key data by converting irregular power turbine rotor speed data and gas turbine outlet temperature data into regular power turbine rotor speed cycle data and gas turbine outlet temperature cycle data, extracting pulsating stress cycle data in the cycle data and using the pulsating stress cycle data for subsequent maximum equivalent stress calculation, and the method is simple in calculation, easy to develop programs and fast in calculation speed compared with the prior art, and the calculation efficiency can be improved while the power turbine disc stress calculation accuracy is ensured.

[0125] Further, the application calculates fatigue damage based on the calculated maximum equivalent stress, adjusts the working state of the aero turbine shaft engine according to the real-time fatigue damage to realize life management of the aero turbine shaft engine, can effectively prolong the service life of the aero turbine shaft engine, and further improves the safety, reliability and maintainability of the aero turbine shaft engine and reduces economic cost.

[0126] The application has been applied in actual engineering, and it only takes 25 milliseconds to solve flight data of a time length of 31 minutes and 55 seconds, which is about 23 times faster than 573 milliseconds required by the traditional method, and the accuracy is 100%, thus proving the beneficial effects of the application.

[0127] Those skilled in the art will appreciate that embodiments of the application can be devised for a method, a system, or a computer program product. Accordingly, the present application can be embodied in the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present application can take the form of a computer program product on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROMs, optical storage devices, etc.) embodying computer readable program code.

[0128] The present application is described in reference to the flowchart and / or block diagrams of the method, apparatus (system) and computer program product according to embodiments of the application. It will be understood that each block of the flowchart and / or block diagrams, and combinations of blocks in the flowchart and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart and / or block diagram block or blocks. Figure 1 one or more functions specified in the flowchart and / or block diagram block or blocks. Figure 1 one or more functions specified in the flowchart and / or block diagram block or blocks.

[0129] These computer program instructions can also be stored in a computer- readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instructions which implement the function specified in the flowchart and / or block diagram block or blocks. Figure 1 one or more functions specified in the flowchart and / or block diagram block or blocks. Figure 1 one or more functions specified in the flowchart and / or block diagram block or blocks.

[0130] These computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart and / or block diagram block or blocks. Figure 1 one or more functions specified in the flowchart and / or block diagram block or blocks. ​ one or more functions specified in the flowchart and / or block diagram block or blocks.

[0131] Obviously, the above-described embodiments are only examples and are not intended to limit the present application. Based on the above description, those skilled in the art can make other variations and modifications of the present application without deviating from the scope of the present application. Therefore, the present application should not be limited by the above embodiments.

Claims

1. A method for calculating the stress cycle of a power turbine disk, characterized in that, include: Acquire power turbine rotor speed data and gas turbine outlet temperature data during the operation of an aero-turbine turbine shaft engine. Use a cycle counting method to convert irregular power turbine rotor speed data and gas turbine outlet temperature data into regular power turbine rotor speed cycle data and gas turbine outlet temperature cycle data. Extract pulsating stress cycle data from the cycle data. The stress at key parts of the power turbine rotor at rated speed is calculated based on the pulsating stress cycle data of the power turbine rotor speed. The stress caused by the temperature field at key parts of the power turbine rotor at different speeds other than rated speed is calculated by combining the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature. The centrifugal stress of the power turbine rotor at its maximum speed is calculated based on the stress at key parts of the power turbine rotor at its rated speed. The temperature stress of the power turbine rotor at its maximum speed is calculated by combining the stress caused by the temperature field at key parts of the power turbine rotor at different speeds other than the rated speed. The combined stress of the power turbine rotor at its maximum speed is obtained by combining the centrifugal stress and the temperature stress at its maximum speed. The maximum equivalent stress of the power turbine rotor is obtained based on the multiple components of the combined stress of the power turbine rotor at the maximum speed, using the equivalent stress calculation method. The calculation of the stress at the critical part of the power turbine rotor at rated speed based on the pulsating stress cycle data of the power turbine rotor speed is specifically as follows: based on the pulsating stress cycle data of the power turbine rotor speed, the finite element simulation method is used to calculate multiple stress components at the critical part of the power turbine rotor at rated speed, so as to obtain the stress at the critical part of the power turbine rotor at rated speed. The method of calculating the stress caused by the temperature field at key parts of the power turbine rotor at different speeds other than the rated speed by combining the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature is as follows: by combining the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature, the finite element simulation method is used to calculate multiple stress components caused by the temperature field at key parts of the power turbine rotor at two different speeds other than the rated speed, and the stress caused by the temperature field at key parts of the power turbine rotor at two different speeds other than the rated speed is obtained. The stress at critical locations of the power turbine rotor at rated speed comprises six stress components. Specifically, the stress at critical locations of the power turbine rotor at rated speed is as follows: ， in, This refers to the stress at key components of the power turbine rotor at rated speed. The components represent the stress components of the key parts of the power turbine rotor at rated speed. ij=11 represents the X-axis stress in the X-direction plane, ij=22 represents the Y-axis stress in the Y-direction plane, ij=33 represents the Z-axis stress in the Z-direction plane, ij=12 represents the Y-axis stress in the X-direction plane, ij=23 represents the Z-axis stress in the Y-direction plane, and ij=31 represents the X-axis stress in the Z-direction plane. The stress caused by the temperature field at key components of the power turbine rotor at two different speeds other than the rated speed includes six stress components. The two different speeds are denoted as the first speed and the second speed, with the first speed being greater than the second speed. The stress caused by the temperature field at key components of the power turbine rotor at the first speed is denoted as... The stress caused by the temperature field in key parts of the power turbine rotor at the second rotational speed is , and Specifically: ， ； in, This represents the stress component caused by the temperature field at key parts of the power turbine rotor at its first rotational speed. The components of the stress caused by the temperature field at the key parts of the power turbine rotor at the second rotational speed are represented by ij=11, which represents the X-axis stress in the X-direction plane, ij=22, which represents the Y-axis stress in the Y-direction plane, ij=33, which represents the Z-axis stress in the Z-direction plane, ij=12, which represents the Y-axis stress in the X-direction plane, ij=23, which represents the Z-axis stress in the Y-direction plane, and ij=31, which represents the X-axis stress in the Z-direction plane. Based on the stress at key locations of the power turbine rotor at rated speed, the centrifugal stress of the power turbine rotor at maximum speed is calculated, specifically as follows: Based on the stress components of the key parts of the power turbine rotor at rated speed, the centrifugal stress components of the power turbine rotor at maximum speed are calculated as follows: ， in, This represents the component of centrifugal stress on the power turbine rotor at its maximum speed, where N represents the maximum speed and NP represents the rated speed. The centrifugal stress of the power turbine rotor at its maximum speed is obtained as follows: ， in, The centrifugal stress of the power turbine rotor at its maximum speed; The method for calculating the temperature stress of the power turbine rotor at its maximum speed is as follows: ， in, This indicates the temperature stress of the power turbine rotor at its maximum speed. For maximum speed, The first rotational speed, This is the second rotational speed; Based on the multiple components of the combined stress of the power turbine rotor at its maximum speed, the maximum equivalent stress of the power turbine rotor is obtained using a method for calculating equivalent stress, specifically: The maximum equivalent stress of the power turbine rotor is calculated based on the six components of the combined stress of the power turbine rotor at its maximum speed: ， in, K1 represents the maximum equivalent stress of the power turbine rotor, and K2 represents the adjustment weights. This represents the X-axis stress in the X-direction plane, representing the combined stress of the power turbine rotor at its maximum speed. This represents the Y-axis stress in the Y-direction plane, representing the combined stress of the power turbine rotor at its maximum speed. This represents the Z-axis stress in the Z-direction plane, representing the combined stress of the power turbine rotor at its maximum speed. This represents the Y-axis stress in the X-plane representing the combined stress of the power turbine rotor at its maximum speed. This represents the Z-axis stress in the Y-plane representing the combined stress of the power turbine rotor at its maximum speed. This represents the X-axis stress in the Z-direction plane, which represents the combined stress of the power turbine rotor at its maximum speed.

2. A power turbine disk stress cycle calculation system, characterized in that, Implementing the power turbine disk stress cycle calculation method according to claim 1 includes: The data acquisition module is used to acquire power turbine rotor speed data and gas turbine outlet temperature data during the operation of the aircraft turbine shaft engine; The data extraction module is used to convert irregular power turbine rotor speed data and gas turbine outlet temperature data into regular power turbine rotor speed cyclic data and gas turbine outlet temperature cyclic data using the cyclic counting method, and to extract pulsating stress cyclic data from the cyclic data. The critical component stress calculation module is used to calculate the stress of the critical component of the power turbine rotor at the rated speed based on the pulsating stress cycle data of the power turbine rotor speed. It also calculates the stress caused by the temperature field of the critical component of the power turbine rotor at different speeds other than the rated speed by combining the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature. The composite stress calculation module is used to calculate the centrifugal stress of the power turbine rotor at the maximum speed based on the stress of the key parts of the power turbine rotor at the rated speed, and to calculate the temperature stress of the power turbine rotor at the maximum speed by combining the stress caused by the temperature field of the key parts of the power turbine rotor at different speeds other than the rated speed. The composite stress of the power turbine rotor at the maximum speed is obtained by combining the centrifugal stress and the temperature stress of the power turbine rotor at the maximum speed. The maximum equivalent stress calculation module calculates the maximum equivalent stress of the power turbine rotor based on the multiple components of the combined stress of the power turbine rotor at the maximum speed and the equivalent stress calculation method.

3. An engine life management method, characterized in that: The method for calculating the stress cycle of the power turbine disk as described in claim 1 is used to calculate the maximum equivalent stress of the power turbine rotor when the aero-turbine turbine shaft engine is working in real time. Based on the maximum equivalent stress of the power turbine rotor, the real-time fatigue damage of key parts of the aero-turbine turbine shaft engine is calculated. Based on the real-time fatigue damage, the working state of the aero-turbine turbine shaft engine is adjusted to achieve life management of the aero-turbine turbine shaft engine.

4. An engine life management system, characterized in that, Implementing the engine life management method of claim 3 includes: The data acquisition module is used to acquire power turbine rotor speed data and gas turbine outlet temperature data during the operation of the aircraft turbine shaft engine; The data extraction module is used to convert irregular power turbine rotor speed data and gas turbine outlet temperature data into regular power turbine rotor speed cyclic data and gas turbine outlet temperature cyclic data using the cyclic counting method, and to extract pulsating stress cyclic data from the cyclic data. The critical component stress calculation module is used to calculate the stress of the critical component of the power turbine rotor at the rated speed based on the pulsating stress cycle data of the power turbine rotor speed. It also calculates the stress caused by the temperature field of the critical component of the power turbine rotor at different speeds other than the rated speed by combining the pulsating stress cycle data of the power turbine rotor speed and the pulsating stress cycle data of the gas turbine outlet temperature. The composite stress calculation module is used to calculate the centrifugal stress of the power turbine rotor at the maximum speed based on the stress of the key parts of the power turbine rotor at the rated speed, and to calculate the temperature stress of the power turbine rotor at the maximum speed by combining the stress caused by the temperature field of the key parts of the power turbine rotor at different speeds other than the rated speed. The composite stress of the power turbine rotor at the maximum speed is obtained by combining the centrifugal stress and the temperature stress of the power turbine rotor at the maximum speed. The maximum equivalent stress calculation module calculates the maximum equivalent stress of the power turbine rotor based on the multiple components of the combined stress of the power turbine rotor at the maximum speed and the equivalent stress calculation method. The life management module is used to calculate the real-time fatigue damage of key parts of the aero-turbine turbine shaft engine based on the maximum equivalent stress of the power turbine rotor, and adjust the working state of the aero-turbine turbine shaft engine according to the real-time fatigue damage, thereby realizing life management of the aero-turbine turbine shaft engine.

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