A method and system for compiling a turboprop engine acceleration mission test spectrum

Abstract

The present invention is applicable to the field of aircraft engine test run spectrum compilation, and provides a method and system for compiling an acceleration mission test run spectrum for a turboprop engine, including: formulating an acceleration mission test run spectrum based on the design spectrum and the first overhaul test run spectrum, based on the key component damage equivalence principle; calculating the damage of key components of the acceleration mission test run spectrum based on the formulated acceleration mission test run spectrum; comparing the damage of key components of the turboprop engine in the acceleration mission test run spectrum with the damage in the design spectrum and the first overhaul test run spectrum, so as to determine the acceleration mission test run spectrum. The above method and system comprehensively consider the low-cycle fatigue damage of the turboprop engine under the design spectrum and the mission test run spectrum, the creep damage of the hot end components, and the mechanical load borne by the reducer, and achieve a balance in the assessment degree of the key components of the turboprop engine by the acceleration mission test run spectrum.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation engine test run spectrum compilation, and in particular relates to a method and system for compiling a turboprop engine acceleration mission test run spectrum. Background Art

[0002] In the prior art, for the compilation of turboprop engine acceleration mission test spectrum, the existing method is to use the first overhaul test spectrum as the compilation basis, calculate the creep damage of the first overhaul test spectrum, ensure that the creep damage is not reduced, and convert the engine working state time with smaller creep damage into large state working time according to the damage equivalence principle to obtain the acceleration mission test spectrum. The traditional acceleration mission test spectrum compilation method ensures that the low cycle fatigue damage and creep damage of the turboprop engine are not lower than the first overhaul test spectrum, but does not assess the mechanical damage of the reducer.

[0003] The first overhaul test spectrum of a certain type of turboprop engine is based on the design spectrum. By calculating and analyzing the combined relationship between the engine turbine after-gas temperature and flight altitude, flight Mach number, engine speed and other parameters, the design spectrum of the turboprop engine is converted into the first overhaul test spectrum based on the principle of equivalence of the permanent creep damage and low-cycle fatigue damage of the hot end components. The damage equivalence principle of the first overhaul test spectrum ensures that the creep damage and low-cycle fatigue damage of the key components of the turboprop engine, such as the gas turbine blades, are equivalent to the design spectrum, but the mechanical damage of the turboprop engine reducer is not considered. The turboprop engine reducer is connected to the propeller and the power turbine respectively, and bears a large torque, so the mechanical load of the reducer also needs to be considered. Therefore, it is necessary to establish a method for compiling an accelerated mission test spectrum that comprehensively considers the low-cycle fatigue damage of the key components of the turboprop engine, the creep damage of the hot end components and the mechanical damage of the reducer. Summary of the invention

[0004] In view of the above problems, the present invention aims to solve one of the technical problems existing in the prior art. To this end, the present invention proposes a method for compiling a turboprop engine acceleration mission test spectrum that can take into account low cycle fatigue damage, creep damage of hot end components, and mechanical damage of the reducer.

[0005] In one aspect, the present invention provides a method for compiling a turboprop engine acceleration mission test spectrum, comprising:

[0006] According to the design spectrum and the first overhaul test spectrum, based on the principle of damage equivalence of key components, an accelerated mission test spectrum is formulated;

[0007] Based on the proposed accelerated task test spectrum, calculate the damage of key components of the accelerated task test spectrum;

[0008] The damage of key components of turboprop engines in the accelerated mission test spectrum is compared with the damage in the design spectrum and the first overhaul test spectrum to determine the accelerated mission test spectrum.

[0009] Furthermore, according to the design spectrum and the first overhaul test spectrum, based on the principle of equivalent damage to key components, the accelerated task test spectrum is proposed, including:

[0010] Analyze the use of turboprop engine design spectra and first overhaul test spectra, and determine the compilation principles and methods of accelerated mission test spectra;

[0011] According to the compilation principles and methods of accelerated mission test spectrum, analyze the damage of key components under the design spectrum and first overhaul test spectrum;

[0012] Based on the damage to key components, an accelerated mission test spectrum is drawn up.

[0013] Furthermore, the damage to key components of the acceleration task test spectrum is calculated including:

[0014] Calculate the creep damage of hot end components based on the service time and endurance life under various working conditions in the proposed accelerated mission test spectrum;

[0015] According to the state time of each state of the acceleration task test spectrum and the propeller speed and torque, the mechanical damage of the reducer of the acceleration task test spectrum is calculated.

[0016] Furthermore, the specific steps for determining the acceleration task vehicle spectrum include:

[0017] The creep damage of the hot end components is compared with the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is compared with the design spectrum reducer mechanical damage and the mechanical damage of the first overhaul test spectrum, and the acceleration task test spectrum is determined based on the comparison results.

[0018] Furthermore, the specific steps of determining the acceleration task test spectrum according to the comparison result include:

[0019] If the creep damage of the hot end components is not less than the calculated value of the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is between the calculated value of the mechanical damage of the reducer in the design spectrum and the calculated value of the mechanical damage of the reducer in the first overhaul test spectrum, then it is determined that the currently proposed acceleration task vehicle spectrum meets the requirements;

[0020] Otherwise, adjust the time of the small damage state of the acceleration task test spectrum and re-draft the acceleration task test spectrum.

[0021] Furthermore, damage to key components also includes damage to turbine blades.

[0022] In another aspect, the present invention further provides a system for compiling an engine acceleration task test spectrum, comprising:

[0023] Proposal unit, calculation unit, determination unit;

[0024] Among them, the drafting unit is used to draft the accelerated task test spectrum based on the design spectrum and the first overhaul test spectrum and the principle of key component damage equivalence;

[0025] The calculation unit is used to calculate the damage of key components of the design spectrum, the first overhaul test spectrum and the acceleration task test spectrum. The damage of key components includes the damage of turbine blades and the mechanical damage of reducer;

[0026] The determination unit is used to compare the damage of key components of the turboprop engine in the accelerated mission test spectrum with the damage in the design spectrum and the first overhaul test spectrum, so as to determine the accelerated mission test spectrum.

[0027] Furthermore, the proposed unit is specifically used for:

[0028] Analyze the use of turboprop engine design spectra and first overhaul test spectra, and determine the compilation principles and methods of accelerated mission test spectra;

[0029] According to the compilation principles and methods of accelerated mission test spectrum, analyze the damage of key components under the design spectrum and first overhaul test spectrum;

[0030] Based on the damage to key components, an accelerated mission test spectrum is drawn up.

[0031] Furthermore, the computing unit is specifically used for:

[0032] Calculate the creep damage of hot end components based on the service time and endurance life under various working conditions in the proposed accelerated mission test spectrum;

[0033] According to the state time of each state of the acceleration task test spectrum and the propeller speed and torque, the mechanical damage of the reducer of the acceleration task test spectrum is calculated.

[0034] Furthermore, the determination unit is specifically used for:

[0035] The creep damage of the hot end components is compared with the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is compared with the design spectrum reducer mechanical damage and the mechanical damage of the first overhaul test spectrum, and the acceleration task test spectrum is determined based on the comparison results.

[0036] The beneficial effects of the present invention are as follows: the compilation method of the present invention comprehensively considers the low-cycle fatigue damage of the turboprop engine under the design spectrum and the mission test spectrum, the creep damage of the hot end components and the mechanical load borne by the reducer, improves the problem that the acceleration mission test spectrum compiled by the traditional method does not take the mechanical damage of the reducer into consideration, and achieves a balance in the degree of assessment of the key components of the turboprop engine by the acceleration mission test spectrum. The method is clear and easy to operate, and provides a basis for considering the reliability and durability of the turboprop engine.

[0037] Other features and advantages of the present invention will be described in the following description or understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 A flow chart of a method for compiling a turboprop engine acceleration mission test spectrum according to an embodiment of the present invention is shown;

[0040] Figure 2 A flowchart showing the specific steps of a method for compiling a turboprop engine acceleration mission test spectrum according to an embodiment of the present invention is shown;

[0041] Figure 3 A block diagram of a turboprop engine acceleration mission test spectrum compilation system according to an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0043] like Figure 1 As shown, the method for compiling an engine acceleration mission test spectrum includes: formulating an acceleration mission test spectrum based on the design spectrum and the first overhaul test spectrum and the principle of equivalent damage to key components; calculating the damage to key components of the acceleration mission test spectrum based on the proposed acceleration mission test spectrum; comparing the damage to key components of the turboprop engine in the acceleration mission test spectrum with the damage in the design spectrum and the first overhaul test spectrum, thereby determining the acceleration mission test spectrum.

[0044] like Figure 2As shown in the figure, in the method for compiling a mission test run spectrum, the preparation of an accelerated mission test run spectrum specifically includes: analyzing the use of the turboprop engine design spectrum and the first overhaul test run spectrum, and determining the principles and methods for compiling the accelerated mission test run spectrum; analyzing the damage of key components under the design spectrum and the first overhaul test run spectrum according to the principles and methods for compiling the accelerated mission test run spectrum; and formulating an accelerated mission test run spectrum based on the damage of key components.

[0045] Among them, the compilation principle of the turboprop engine acceleration mission test spectrum is as follows: low cycle fatigue is the main damage factor of the engine wheel disc, and the acceleration mission test spectrum must ensure that the low cycle fatigue damage assessment is not reduced; the large state working time is the key factor affecting the life of hot end components such as the engine gas turbine blades, and the acceleration mission test spectrum must ensure that the large state time is not less than the first overhaul test spectrum, and some small states can be equivalent to the large state through the damage equivalence principle; when the engine is started, the acceleration rate from slow speed to the middle and above states determines the thermal gradient of components such as the turbine disc. In order to ensure that the damage rate is consistent with the external field, the acceleration rate of the acceleration process of the acceleration mission test spectrum must be consistent with the external field usage; in addition to the equivalence of low cycle damage and thermal load damage, the mechanical load of the acceleration mission test spectrum must also be equivalent to the usage spectrum.

[0046] Among them, the method for compiling the acceleration mission test spectrum of the turboprop engine is that the number of "slow start-takeoff-slow start" cycles remains basically unchanged to ensure that the low cycle fatigue damage of the acceleration mission test spectrum is equivalent to the first overhaul test spectrum; in the compilation of the acceleration mission test spectrum, it is ensured that the large state time is not less than the first overhaul test spectrum, and some small states can be equivalent to the large state through creep damage to ensure that the creep damage of the gas turbine blade is not lower than the first overhaul test spectrum; the small state is equivalent to the time of the large state according to the reducer torque to ensure that the mechanical load is equivalent.

[0047] Calculating the damage of key components of the accelerated mission test spectrum specifically includes: calculating the creep damage of the hot end components of the first overhaul test spectrum according to the working time of each state of the first overhaul test spectrum and the endurance life under the working condition; calculating the mechanical damage of the reducer in the design spectrum and the first overhaul test spectrum according to the propeller speed, torque and working time under each working condition; comparing and analyzing the damage of key components under the accelerated mission test spectrum with the damage of key components under the design spectrum and the first overhaul test spectrum, and finally determining the accelerated mission test spectrum that is more reasonable for the assessment of low cycle fatigue damage, creep damage and mechanical damage of the turboprop engine.

[0048] The calculation of creep damage of hot end components under various states is as follows: Assuming that the engine works for m hours in a certain state i In this state, the endurance life of the gas turbine blade is N i , then the working damage s of the gas turbine blade in this state i for:

[0049]

[0050] According to formula (1), the damage of the gas turbine blades under n engine states is calculated respectively, and the total damage s of the gas turbine blades under n working states of the spectrum line is accumulated to obtain s i =∑s i (i=1,2,...n).

[0051] The calculation of the mean cubic root equivalent torque and equivalent time of the reducer is as follows: According to the propeller speed and output torque under each state of the aircraft design spectrum and the first overhaul test spectrum, combined with the working state time of each engine, the mean cubic root equivalent torque is calculated. The calculation formula of the mean cubic root equivalent torque in the reducer power spectrum is:

[0052]

[0053] Formula (2): T d — Design power spectrum or test power spectrum mean cubic root equivalent torque, Nm; T i —Torque of the i-th state in the design power spectrum or test power spectrum, Nm; t i —The time of the i-th state in the design power spectrum or test power spectrum; n—The total number of load states in the design power spectrum or test power spectrum.

[0054] The calculation formula of the reducer acceleration equivalent coefficient is:

[0055]

[0056] In formula (3): K is the acceleration equivalent coefficient of the test spectrum relative to the design power spectrum; T d1 —Test spectrum mean cubic root equivalent torque, Nm; T d0 —Design spectrum mean cube root equivalent torque, Nm.

[0057] Determine the equivalent time by the acceleration equivalent coefficient: t d =K×t(4), where: t d —equivalent time, h; K—acceleration equivalent coefficient of the test spectrum relative to the power spectrum used; t—actual test time, h.

[0058] The specific steps of determining the acceleration task test run spectrum include: comparing the creep damage of the hot end components of the acceleration task test run spectrum with the creep damage of the hot end components of the first overhaul test run spectrum, comparing the mechanical damage of the reducer with the mechanical damage of the reducer in the design spectrum and the first overhaul test run spectrum, and determining the acceleration task test run spectrum according to the comparison result. Among them, the specific steps of determining the acceleration task test run spectrum according to the comparison result include: if the creep damage of the hot end components is not less than the damage value of the hot end components in the first overhaul test run spectrum, and the mechanical damage of the reducer is between the calculated value of the mechanical damage of the reducer in the design spectrum and the calculated value of the mechanical damage of the reducer in the first overhaul test run spectrum, then it is determined that the currently proposed acceleration task test run spectrum meets the requirements; otherwise, adjust the time of the small damage state of the acceleration task test run spectrum, and re-plan the acceleration task test run spectrum. It should be noted that the preparation of the first overhaul test spectrum does not take into account the mechanical load on the reducer. Therefore, it is necessary to calculate the mean cubic root equivalent torque and acceleration equivalent coefficient of the reducer in the design spectrum and the first overhaul test spectrum according to the propeller output torque and working time in each state of the engine, and compare and analyze the equivalent working time of the reducer to provide a basis for considering the damage of the reducer in the preparation of the acceleration mission test spectrum; the reducer of the turboprop engine is connected to the propeller and the turbine respectively, and the mechanical load it is subjected to is large. Therefore, according to the time of each state of the acceleration mission test spectrum, combined with the propeller mean cubic root equivalent torque and equivalent time, the damage of the reducer is assessed, and the damage is compared with the damage of the reducer in the design spectrum and the first overhaul test spectrum to achieve appropriate assessment of the mechanical damage of the turboprop engine reducer.

[0059] Among them, the design spectrum is a load spectrum for the design of new aircraft. The design spectrum is a kind of predicted spectrum, which can be inferred from the load spectrum of the current aircraft with the same mission and similar structure by experience; it can also be obtained by mixing the predicted flight profile and the predicted mission. The typical mission profile of the design spectrum contains information such as flight altitude, speed and engine working state, while the first overhaul test assessment of the engine is carried out on the ground bench, which cannot simulate the flight altitude and speed. Therefore, the working state of the engine in flight must be equivalent to the working state under the ground bench. Analyze the characteristics of each typical mission profile of the design spectrum, merge the mission profiles according to their characteristics, and determine the mission profile of the first overhaul test spectrum. The compilation of the first overhaul test spectrum is based on the engine installation and use requirements and the engine performance calculation results, ensuring that the proportion of the large state working time of the first overhaul test spectrum is slightly greater than or equal to the proportion of the large state time in the typical mission profile; the number of cycles consumed by the test spectrum is basically equivalent to the low cycle number in the design load spectrum; the air state is equivalent to the bench test state according to the principle of merging the rotor speed of the engine gas generator and the Tt45 temperature. It should be noted that to obtain the engine's first overhaul test spectrum, it is necessary to summarize and analyze the various spectral lines of the engine's design spectrum, including analyzing the engine's design spectrum working status, each state time, and the total number of stages.

[0060] Among them, the use of turboprop engine design spectrum and mission test spectrum is analyzed, including: the field design spectrum and first overhaul test spectrum give the engine state, duration, frequency of the engine's typical mission profile, as well as the combustion rotor speed and propeller speed of each state, and count the total number of stages and total test time of the design spectrum and first overhaul test spectrum; statistically analyze the time of each state in each mission spectrum line, and then classify and merge the time of each engine state according to the mission frequency, and analyze its proportion of the total time, so as to provide a reference for determining the time of each engine state and calculating the damage in the compilation of accelerated mission test spectrum.

[0061] Among them, the compilation principles and methods of the acceleration task test run spectrum are determined according to the fatigue damage characteristics of key components, including: analyzing and clarifying the key engine components to be considered in the compilation of the acceleration task test run spectrum. The key parts of the engine test run assessment are generally the hot end components, such as: gas turbine rotor blades and wheels. In addition, the left and right ends of the turboprop engine reducer are connected to the power turbine and propeller respectively, and the torque is large, so the workload of the reducer also needs to be considered; according to the key components to be considered in the compilation of the acceleration task test run spectrum, the main factors affecting the damage of the key components are clarified, so as to formulate the compilation principles of the turboprop engine acceleration task test run spectrum to be compiled; on the basis of the formulated acceleration task test run spectrum compilation principles, ensure that the assessment level of the factors that have a major impact on the damage of key components is not reduced, and formulate a compilation method for the acceleration task test run spectrum based on the first overhaul test run spectrum.

[0062] Among them, the damage of key components under each working state in the design spectrum and the first overhaul test spectrum is analyzed, including: the first overhaul test spectrum of the engine ensures that the low-cycle fatigue damage of key components and the creep damage of hot-end components are not less than the design spectrum, so here the damage of hot-end components under each state is calculated mainly based on the service time under each working condition of the first overhaul test spectrum and the endurance life; the preparation of the first overhaul test spectrum does not take into account the mechanical load borne by the reducer, so it is necessary to calculate the equivalent torque and acceleration equivalent coefficient of the reducer in the design spectrum and the first overhaul test spectrum according to the propeller speed, output torque and working time of each state of the engine, and compare and analyze the equivalent working time of the reducer, so as to provide a basis for considering the damage of the reducer in the preparation of the acceleration mission test spectrum.

[0063] Among them, the acceleration task test spectrum is compiled. According to the compilation principles and compilation methods of the acceleration task test spectrum, the number of cycle stages of the acceleration task test spectrum and the ratio of environmental mixing are determined based on the first overhaul test spectrum, and the running time of the engine state with less damage to the key components of the hot end in the test spectrum is reduced, such as: low-power running time, but it is necessary to ensure that the assessment of thermal fatigue is not reduced; since the reducer of the turboprop engine is connected to the propeller and turbine respectively, the mechanical load is large, so here according to the obtained acceleration task test spectrum of each state time, combined with the reducer mean cube root equivalent torque and equivalent time, the damage of the reducer is assessed, and the damage is compared with the design spectrum and the damage of the reducer of the first overhaul test spectrum, until the creep damage of the hot end component is not less than the first overhaul test spectrum, and the mechanical damage of the reducer is not less than the design spectrum but not more than the first overhaul test spectrum. At this time, it can be considered that the acceleration task test spectrum is relatively reasonable for the assessment of the key components of the turboprop engine; based on the running time of the engine in each state, combined with the number of cycle stages to determine the duration of the single-frequency working state, the acceleration task test spectrum is compiled.

[0064] It should be noted that the engine first overhaul test spectrum ensures that the low-cycle fatigue damage of key components and the creep damage of hot-end components are not less than the design spectrum, so the calculation of the creep damage of hot-end components under various states is mainly based on the service time and endurance life under various working conditions of the first overhaul test spectrum; the calculation of the mechanical damage of the reducer includes calculating the mean cube root equivalent torque and acceleration equivalent coefficient of the reducer in the design spectrum and the first overhaul test spectrum, and comparing and analyzing the equivalent working time of the reducer, providing a basis for considering the damage of the reducer in the preparation of the acceleration mission test spectrum. This method simultaneously assesses the low-cycle fatigue damage, creep damage of hot-end components and the mechanical load borne by the reducer, improving the problem that the turboprop engine acceleration mission test spectrum compiled according to the existing traditional method does not consider the mechanical damage of the reducer.

[0065] After calculating the damage of key components of the accelerated mission test spectrum, assess the damage of key components of the preliminarily proposed test spectrum, and compare the damage with the damage of the design spectrum and the first overhaul test spectrum. If the thermal fatigue damage of the hot end component is not less than the first overhaul test spectrum, and the mechanical damage of the reducer is not less than the design spectrum but not greater than the first overhaul test spectrum, the duration of the single-frequency working state can be determined in combination with the number of cycle stages to determine the accelerated mission test spectrum. At this time, it can be considered that the accelerated mission test spectrum is relatively reasonable for the assessment of key components of the turboprop engine; if the thermal fatigue damage of the hot end component is less than the first overhaul test spectrum or the mechanical damage of the reducer is less than the design spectrum, adjust the time of the small damage state of the accelerated mission test spectrum, calculate the damage of the key component again, and compare the damage with the design spectrum and the first overhaul test spectrum again to determine whether the accelerated mission test spectrum is determined.

[0066] like Figure 3As shown, the compilation system of the engine acceleration task test spectrum includes: a drafting unit, a calculation unit, and a determination unit. Among them, the drafting unit is specifically used to draft the acceleration task test spectrum according to the use of the design spectrum and the first overhaul test spectrum, and according to the principles and methods of determining the acceleration task test spectrum; the calculation unit is specifically used to calculate the creep damage of the hot end components according to the first overhaul test spectrum, and calculate the mechanical damage of the reducer according to the engine design spectrum and the first overhaul test spectrum; the determination unit is specifically used to compare the creep damage of the hot end components with the creep damage of the hot end components in the first overhaul test spectrum, and compare the mechanical damage of the reducer with the mechanical damage of the reducer in the design spectrum and the first overhaul test spectrum, so as to determine the acceleration task test spectrum.

[0067] The present invention provides a method for compiling a turboprop engine acceleration mission test spectrum, which is used for compiling an acceleration mission test load spectrum related to a turboprop engine ground test, and provides a basis for evaluating the reliability and durability of the turboprop engine. According to the method for compiling a turboprop engine acceleration mission test spectrum according to an embodiment of the present invention, compared with the prior art solution, the acceleration mission test spectrum compiled according to the method of the present invention comprehensively considers the low-cycle fatigue damage, the creep damage of the hot end components and the mechanical load borne by the reducer under the design spectrum and the mission test spectrum, improves the problem that the acceleration mission test spectrum compiled according to the traditional method does not consider the mechanical damage of the reducer, and achieves the balance of the acceleration mission test spectrum on the assessment degree of the key components of the turboprop engine. The method is clear and easy to operate, and provides a basis for evaluating the reliability and durability of the turboprop engine. Compared with the method for compiling a turboprop engine acceleration mission test spectrum based only on the first overhaul test spectrum, the method also considers the engine design spectrum. The acceleration mission test spectrum compiled according to the method is more reasonable for the reliability assessment of the key components of the engine, and has strong versatility and engineering application value for turboprop engines.

[0068] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for compiling a turboprop engine acceleration mission test spectrum, comprising: According to the design spectrum and the first overhaul test spectrum, based on the principle of damage equivalence of key components, an accelerated mission test spectrum is formulated; Based on the proposed accelerated task test spectrum, calculate the damage of key components of the accelerated task test spectrum; The damage of key components of turboprop engines in the accelerated mission test spectrum is compared with the damage in the design spectrum and the first overhaul test spectrum to determine the accelerated mission test spectrum.

2. A method for compiling a turboprop engine acceleration mission test spectrum according to claim 1, wherein: According to the design spectrum and the first overhaul test spectrum, based on the principle of equivalent damage to key components, the accelerated task test spectrum is proposed, including: Analyze the use of turboprop engine design spectra and first overhaul test spectra, and determine the compilation principles and methods of accelerated mission test spectra; According to the compilation principles and methods of accelerated mission test spectrum, analyze the damage of key components under the design spectrum and first overhaul test spectrum; Based on the damage to key components, an accelerated mission test spectrum is drawn up.

3. A method for compiling a turboprop engine acceleration mission test spectrum according to claim 1, wherein: The damage to key components of the calculation acceleration task test spectrum includes: Calculate the creep damage of hot end components based on the service time and endurance life under various working conditions in the proposed accelerated mission test spectrum; According to the state time of each state of the acceleration task test spectrum and the propeller speed and torque, the mechanical damage of the reducer of the acceleration task test spectrum is calculated.

4. A method for compiling a turboprop engine acceleration mission test spectrum according to claim 3, wherein: The specific steps for determining the acceleration task vehicle spectrum include: The creep damage of the hot end components is compared with the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is compared with the design spectrum reducer mechanical damage and the mechanical damage of the first overhaul test spectrum, and the acceleration task test spectrum is determined based on the comparison results.

5. A method for compiling a turboprop engine acceleration mission test spectrum according to claim 4, wherein: The specific steps of determining the acceleration task test spectrum based on the comparison results include: If the creep damage of the hot end components is not less than the calculated value of the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is between the calculated value of the mechanical damage of the reducer in the design spectrum and the calculated value of the mechanical damage of the reducer in the first overhaul test spectrum, then it is determined that the currently proposed acceleration task vehicle spectrum meets the requirements; Otherwise, adjust the time of the small damage state of the acceleration task test spectrum and re-draft the acceleration task test spectrum.

6. A method for compiling a turboprop engine acceleration mission test spectrum according to any one of claims 1 to 5, wherein: Damage to key components also includes damage to turbine blades.

7. A turboprop engine acceleration mission test spectrum compilation system, comprising: Proposal unit, calculation unit, determination unit; Among them, the drafting unit is used to draft the accelerated task test spectrum based on the design spectrum and the first overhaul test spectrum and the principle of key component damage equivalence; The calculation unit is used to calculate the damage of key components of the design spectrum, the first overhaul test spectrum and the acceleration task test spectrum. The damage of key components includes the damage of turbine blades and the mechanical damage of reducer; The determination unit is used to compare the damage of key components of the turboprop engine in the accelerated mission test spectrum with the damage in the design spectrum and the first overhaul test spectrum, so as to determine the accelerated mission test spectrum.

8. A turboprop engine acceleration mission test spectrum compilation system according to claim 7, wherein: The proposed unit is specifically intended for: Analyze the use of turboprop engine design spectra and first overhaul test spectra, and determine the compilation principles and methods of accelerated mission test spectra; According to the compilation principles and methods of accelerated mission test spectrum, analyze the damage of key components under the design spectrum and first overhaul test spectrum; Based on the damage to key components, an accelerated mission test spectrum is drawn up.

9. A turboprop engine acceleration mission test spectrum compilation system according to claim 7 or 8, wherein: The computing unit is specifically used for: Calculate the creep damage of hot end components based on the service time and endurance life under various working conditions in the proposed accelerated mission test spectrum; According to the state time of each state of the acceleration task test spectrum and the propeller speed and torque, the mechanical damage of the reducer of the acceleration task test spectrum is calculated.

10. A turboprop engine acceleration mission test spectrum compilation system according to claim 9, wherein: Determine the unit specifically for: The creep damage of the hot end components is compared with the creep damage of the hot end components in the first overhaul test spectrum, and the mechanical damage of the reducer is compared with the design spectrum reducer mechanical damage and the mechanical damage of the first overhaul test spectrum, and the acceleration task test spectrum is determined based on the comparison results.

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