Aviation turboshaft engine design load spectrum compilation reference object analysis method

Abstract

The invention relates to the technical field of aviation turbine shaft engines, and provides an aviation turbine shaft engine design load spectrum compilation reference object analysis method, which comprises the following steps of: counting high-power states of engines corresponding to air typical mission profiles of various helicopters and high-power state use time of the engines according to information of the typical mission profiles; calculating a high-power state cumulative time ratio of an engine in a typical mission profile related to each type of helicopter; based on the high-power state cumulative time proportion of the engine, calculating the high-power state reduced time proportion of the engine in all typical mission profiles of various helicopters; and selecting a helicopter as a load spectrum compiling reference object according to the high-power state-to-time ratio of the engine, and compiling a load spectrum based on the helicopter. According to the method, through effective and simple engine power state comparative analysis, a proper helicopter platform is selected as a design object, and the obtained design load spectrum can meet the use requirements of all helicopter platforms.

Description

Technical Field

[0001] The invention relates to the technical field of aviation turboshaft engines, and in particular to a reference object analysis method for compiling a design load spectrum of an aviation turboshaft engine. Background Art

[0002] The load spectrum is the time history of the typical load borne by the whole machine or parts. It is a general term for the graphs, tables, matrices and other probabilistic eigenvalues ​​that represent the relationship between the load size and the frequency of occurrence after sorting and statistical processing. The design load spectrum is a load spectrum used for aircraft engine design and testing. It is a kind of predicted spectrum that can be obtained by mixing the predicted flight mission profile and the predicted mission. The structural failure of the aircraft engine is likely to cause serious flight safety accidents. The main reason is that the service strength and life of the engine are overestimated. The strength and life analysis and test verification of the aircraft engine all rely on the design load spectrum. Therefore, the preparation of the design load spectrum is very important in the field of aircraft engine development.

[0003] At present, the existing load spectrum design methods mainly focus on the flight load spectrum statistical method based on rain flow counting, the typical mission profile mixing method or the comprehensive method of the two. However, the above load spectrum compilation methods are all carried out for the engine on a single installation platform, focusing on the specific basic elements of the load spectrum such as cycle statistics, mission mixing, and environmental mixing. With the development of helicopter series, it has become a mainstream trend for multiple helicopters to use the same type of engine. Therefore, in the design of engine load spectrum, only considering a single installation platform object can no longer reliably guarantee the load capacity and safe use requirements of multiple helicopters for the engine. Therefore, how to select a suitable reference object to carry out load spectrum compilation, so as to obtain a load spectrum that can meet the use requirements of all helicopter platforms is a problem that needs to be solved urgently. Summary of the invention

[0004] The purpose of the present invention is to solve at least one technical problem in the background technology and to provide a reference object analysis method for compiling a design load spectrum for an aviation turboshaft engine.

[0005] To achieve the above object, the present invention provides a reference object analysis method for compiling a design load spectrum of an aviation turboshaft engine, comprising: Obtain the typical mission profiles of various types of helicopters, and count the high-power state of the engine and the high-power state usage time of the engine corresponding to the typical mission profiles of various types of helicopters in the air based on the information of each typical mission profile; Calculate the cumulative time percentage of the engine in high-power state in the typical mission profiles of each type of helicopter; Based on the cumulative proportion of the engine's high-power state time, calculate the proportion of the engine's high-power state time in all typical mission profiles of various types of helicopters; According to the time proportion of the engine's high-power state, a helicopter is selected as a reference object for load spectrum compilation, and the load spectrum is compiled based on the helicopter.

[0006] According to one aspect of the present invention, the high power state of the engine includes: a maximum state, an intermediate state and a maximum continuous state; The high-power state use time of the engine includes: the use time of the maximum state, the use time of the intermediate state and the use time of the maximum continuous state.

[0007] According to one aspect of the present invention, the cumulative time proportion of the engine in the high-power state in the typical mission profile involved in each type of helicopter is calculated, including: Calculate the time percentage of a high-power state of an engine for a single mission profile: ; Calculate the cumulative proportion of the engine's high-power state time in all mission profiles involved in each type of helicopter: ; Where n represents the number of categories of typical mission profiles performed by a certain type of helicopter.

[0008] According to one aspect of the present invention, based on the cumulative time proportion of the high-power state of the engine, the high-power state equivalent time proportion of the engine in all typical mission profiles of various types of helicopters is calculated as follows: The proportion of the engine's high-power state in all tasks = the cumulative proportion of the engine's maximum state in all tasks × +The percentage of engine intermediate state time accumulated in all missions× +The maximum continuous state cumulative time ratio of the engine in all tasks× ; in, , , are the weight coefficients of the maximum state, intermediate state, and maximum continuous state, respectively, and : : =4:2:1.

[0009] According to one aspect of the present invention, the helicopter selected as the reference object for load spectrum compilation according to the high-power state equivalent time proportion of the engine is: A type of helicopter with the highest proportion of engine high-power state time was selected as the reference object for load spectrum compilation.

[0010] According to the solution of the present invention, the present invention provides a method for analyzing and selecting a reference object (helicopter) for design load spectrum compilation when a type of aviation turboshaft engine is installed and used on multiple types of helicopter platforms with different purposes (one machine for multiple purposes), and then compiling a load spectrum based on the reference object. The present invention selects a type of helicopter platform with the largest proportion of engine high-power state time as the design object through effective and simple comparative analysis of engine power states, and the obtained design load spectrum can meet the use requirements of all helicopter platforms. It can be seen that the present invention provides an effective solution to the problem of compiling design load spectra when a type of engine is installed on multiple types of helicopter platforms for use. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The flowchart schematically shows a reference object analysis method for compiling a design load spectrum of an aviation turboshaft engine according to an embodiment of the present invention. DETAILED DESCRIPTION

[0012] The present invention will now be discussed with reference to exemplary embodiments. It should be understood that the embodiments discussed are only to enable those skilled in the art to better understand and thus implement the present invention, rather than implying any limitation on the scope of the present invention.

[0013] As used herein, the term “including” and variations thereof are to be interpreted as open-ended terms meaning “including, but not limited to.” The term “based on” is to be interpreted as “based, at least in part, on.” The terms “one embodiment” and “an embodiment” are to be interpreted as “at least one embodiment.”

[0014] Figure 1 The flowchart schematically shows a reference object analysis method for compiling a design load spectrum of an aviation turboshaft engine according to an embodiment of the present invention. Figure 1 As shown, in this embodiment, the reference object analysis method for compiling the design load spectrum of an aviation turboshaft engine includes: Obtain the typical mission profiles of various types of helicopters, and count the high-power state of the engine and the high-power state usage time of the engine corresponding to the typical mission profiles of various types of helicopters in the air based on the information of each typical mission profile; Calculate the cumulative time percentage of the engine in high-power state in the typical mission profiles of each type of helicopter; Based on the cumulative proportion of the engine's high-power state time, calculate the proportion of the engine's high-power state time in all typical mission profiles of various types of helicopters; According to the time proportion of the engine's high-power state, a helicopter is selected as a reference object for load spectrum compilation, and the load spectrum is compiled based on the helicopter.

[0015] In this embodiment, the profile information of a typical mission profile mainly includes flight status, flight altitude, ambient temperature, time, helicopter bleed air, and mission mixing.

[0016] Further, according to an embodiment of the present invention, the high power state of the engine includes: a maximum state, an intermediate state, and a maximum continuous state; The engine's high-power state usage time includes: maximum state usage time, intermediate state usage time and maximum continuous state usage time.

[0017] In this embodiment, the power requirements corresponding to the typical mission profiles of various types of helicopters in the air are calculated and analyzed based on the typical profile information obtained. The engine performance model is used to calculate and analyze the corresponding engine usage status. Since more than 90% of the damage to the engine is determined by the maximum continuous and above power states and their duration, the present invention focuses on counting the engine high-power state and the corresponding time, that is, the above-mentioned maximum state, intermediate state and maximum continuous state, as well as the usage time of the maximum state, the usage time of the intermediate state and the usage time of the maximum continuous state.

[0018] Further, according to an embodiment of the present invention, the cumulative time proportion of the engine in the high-power state in the typical mission profile involved in each type of helicopter is calculated, including: Calculate the time percentage of a high-power state of an engine for a single mission profile: ; Calculate the cumulative proportion of the engine's high-power state time in all mission profiles involved in each type of helicopter: ; Where n represents the number of categories of typical mission profiles performed by a certain type of helicopter.

[0019] In this embodiment, according to the above method, the cumulative time proportion of the engine high-power state in the typical mission profile of a certain type A, type B, and type C helicopter equipped with a certain type of aviation turboshaft engine can be obtained respectively.

[0020] Further, according to an embodiment of the present invention, based on the cumulative time proportion of the engine in the high-power state, the equivalent time proportion of the engine in the high-power state in all typical mission profiles of various types of helicopters is calculated as follows: The proportion of the engine's high-power state in all tasks = the cumulative proportion of the engine's maximum state in all tasks × +The percentage of engine intermediate state time accumulated in all missions× +The maximum continuous state cumulative time ratio of the engine in all tasks× ; in, , , are the weight coefficients of the maximum state, intermediate state, and maximum continuous state, respectively, and : : =4:2:1.

[0021] In this embodiment, according to the above method, the equivalent time proportion of the high-power state of the engine corresponding to the A-type, B-type, and C-type helicopters can be obtained.

[0022] Further, according to an embodiment of the present invention, the helicopter selected as the reference object for load spectrum compilation according to the high-power state equivalent time proportion of the engine is: A type of helicopter with the highest proportion of engine high-power state time was selected as the reference object for load spectrum compilation.

[0023] In this embodiment, a type of helicopter with the highest proportion of high-power state time is selected as a reference object for load spectrum compilation, and then the subsequent specific design load spectrum compilation work is carried out. For example, among the three types of helicopters mentioned above, the type A helicopter has the largest proportion of engine high-power state time, so the type A helicopter is selected as the reference object for load spectrum compilation, and the obtained design load spectrum can meet the use requirements of all helicopter platforms.

[0024] According to the above scheme of the present invention, the present invention provides a method for analyzing and selecting a reference object (helicopter) for design load spectrum compilation when a type of aviation turboshaft engine is installed and used on multiple types of helicopter platforms with different purposes (one machine for multiple purposes), and then compiling a load spectrum based on the reference object. The present invention selects a type of helicopter platform with the largest proportion of engine high-power state time as the design object through effective and simple comparative analysis of engine power states, and the obtained design load spectrum can meet the use requirements of all helicopter platforms. It can be seen that the present invention provides an effective solution to the problem of compiling design load spectra when a type of engine is installed on multiple types of helicopter platforms for use.

[0025] Those skilled in the art will appreciate that the modules and algorithm steps described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0026] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with the technical features with similar functions disclosed in this application (but not limited to) by each other.

[0027] It should be understood that the size of the serial numbers of each step in the content of the invention and the implementation methods of the present invention does not absolutely mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the implementation methods of the present invention.

Claims

1. A reference object analysis method for compiling a design load spectrum for an aviation turboshaft engine, characterized in that: include: Obtain the typical mission profiles of various types of helicopters, and count the high-power state of the engine and the high-power state usage time of the engine corresponding to the typical mission profiles of various types of helicopters in the air based on the information of each typical mission profile; Calculate the cumulative time percentage of the engine in high-power state in the typical mission profiles of each type of helicopter; Based on the cumulative proportion of the engine's high-power state time, calculate the proportion of the engine's high-power state time in all typical mission profiles of various types of helicopters; According to the time proportion of the engine's high-power state, a helicopter is selected as a reference object for load spectrum compilation, and the load spectrum is compiled based on the helicopter.

2. The reference object analysis method for compiling design load spectrum of an aviation turboshaft engine according to claim 1, characterized in that: The high-power state of the engine includes: a maximum state, an intermediate state and a maximum continuous state; The high-power state use time of the engine includes: the use time of the maximum state, the use time of the intermediate state and the use time of the maximum continuous state.

3. The reference object analysis method for compiling design load spectrum of an aviation turboshaft engine according to claim 2, characterized in that: Calculate the cumulative time percentage of the engine in high-power state in the typical mission profiles of each type of helicopter, including: Calculate the time percentage of a high-power state of an engine for a single mission profile: ; Calculate the cumulative proportion of the engine's high-power state time in all mission profiles involved in each type of helicopter: ; Where n represents the number of categories of typical mission profiles performed by a certain type of helicopter.

4. The reference object analysis method for compiling design load spectrum of an aviation turboshaft engine according to claim 3, characterized in that: Based on the cumulative time proportion of the engine in high-power state, the equivalent time proportion of the engine in high-power state in all typical mission profiles of various types of helicopters is calculated as follows: The proportion of the engine's high-power state in all tasks = the cumulative proportion of the engine's maximum state in all tasks × +The percentage of engine intermediate state time accumulated in all missions× +The maximum continuous state cumulative time ratio of the engine in all tasks× ; in, , , are the weight coefficients of the maximum state, intermediate state, and maximum continuous state, respectively, and : : =4:2:

1.

5. The reference object analysis method for compiling design load spectrum of an aviation turboshaft engine according to any one of claims 1 to 4, characterized in that: The helicopter selected as the reference object for load spectrum compilation according to the time proportion of the engine's high-power state is: A type of helicopter with the highest proportion of engine high-power state time was selected as the reference object for load spectrum compilation.

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