CN116227148B

CN116227148B - Method for constructing maneuvering overload spectrum of aeroengine

Info

Publication number: CN116227148B
Application number: CN202211740059.5A
Authority: CN
Inventors: 郑茂军; 张勇; 程荣辉; 丛佩红; 曹茂国; 柏汉松
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2022-12-31
Filing date: 2022-12-31
Publication date: 2024-02-02
Anticipated expiration: 2042-12-31
Also published as: CN116227148A

Abstract

The method is used for constructing a maneuvering overload spectrum of a cross-generation new-research model, takes demand analysis as a starting point, is based on cross-generation new-research model design usage analysis, and provides basis for the design and test of important bearing structure life of an engine by collecting, analyzing, absorbing and integrating various existing limitation data conditions so as to construct a maneuvering overload spectrum, so that the problem that the maneuvering overload spectrum of the aircraft engine has no direct design input and cannot be directly obtained by using data statistics of an external field due to large difference of the existing model usage is solved; due to the close fit of the cross-generation model design usage, the construction method can more accurately predict the maneuvering overload spectrum of the engine after service, ensure the design service life and not improve the development difficulty.

Description

Method for constructing maneuvering overload spectrum of aeroengine

Technical Field

The application belongs to the technical field of aeroengines, and particularly relates to a method for constructing an engine power-driven overload spectrum of an aeroengine.

Background

Overload loads (commonly referred to as maneuver loads) under the use scenarios of take-off, landing, maneuver flight, wind gusts, vibration, installation and crash conditions, etc. can affect the design life of the engine load carrying structure, and should be considered in low cycle fatigue life design and test, according to the general specification requirements of the aero-engine.

From the general flow point of new engine development, engine maneuvering overload spectrum is provided to engine development party by user party and airplane party; from the technical point of view, the maneuvering overload spectrum reflects the using degree of the user side on the engine in the external field and is obtained through the statistical analysis of the using data of the same kind of active machine types.

However, due to factors such as large technical span of the new machine, lack of similar machine types, large difference in usage and the like, there are sometimes cases where the maneuver overload spectrum required for development of the new machine cannot be obtained statistically from the usage data of the user, the aircraft side and the current work. In the case of an inorganic dynamic overload spectrum, new machine life designs and tests will be constrained.

In view of the above, the following two solutions are generally adopted in the prior art:

one is to directly apply the motor overload spectrum of the design or use stage of the active machine type, but because the development and use period of the engine are long, the external use method of the active machine type is usually lighter and cannot represent the design use method of the cross-generation machine type, and the use method has obvious difference to the use method of the new machine type and the active machine type in consideration of factors such as the change of tasks and service environment; the method can cause a large gap between the new machine and the same generation machine in the aspect of the maneuverability, and reduces the competitive power of the engine after service;

The other is to adopt a simplified method, namely, based on the dynamic overload spectrum of the active machine type, the design of the bearing structure and the test verification are carried out by improving the reserve coefficient; the method often brings over the service life margin of the bearing structure and causes overweight structure, and the pushing-up ratio is a key index for influencing the use efficiency and agility (mobility) of the product, so that the method also restricts the competitiveness of the product after service.

Disclosure of Invention

The invention aims to provide a method for constructing an aeroengine maneuvering overload spectrum, which solves or reduces at least one problem in the background technology.

The technical scheme of the application is as follows: an aeroengine maneuver load spectrum construction method for constructing maneuver load spectrum of a cross-generation new-research model, comprising:

determining key characteristics of a maneuvering flight load spectrum of the cross-generation new-grinder type by using a demand analysis method, collecting a first type construction basis and a second type construction basis according to the key characteristics of the maneuvering load spectrum of the cross-generation new-grinder type, analyzing element integrality of the first construction basis and the second construction basis, and determining a maneuvering overload range of the second type construction basis;

aiming at a cross-generation new-grinding type maneuvering overload spectrum, listing a normal maneuvering overload range of each construction basis, carrying out comparative analysis on the maneuvering overload range of each construction basis, determining a normal maneuvering overload range, dividing a normal maneuvering overload amplitude into a plurality of intervals according to typical characteristics of maneuvering flight actions and the normal overload range, giving maneuvering flight action characteristics and possible maneuvering action types to each interval, listing a longitudinal or transverse maneuvering overload range of each construction basis according to a matching result of the normal overload amplitude range and the construction basis and a corresponding relation of the longitudinal or transverse overload and the normal overload amplitude range, and determining a corresponding relation of the three-way overload amplitude range;

According to the influence degree of the normal overload amplitude on the service life of the bearing structure, the normal maneuvering overload range is classified into three categories, including small overload, medium overload and large overload; determining the sum of frequencies of normal medium overload and large overload and the frequency distribution of normal large overload, medium overload and small overload, and synthesizing the corresponding relation between the longitudinal or transverse overload and the normal overload amplitude range and the frequency distribution of normal large overload, medium overload and small overload to obtain a maneuvering overload coefficient spectrum;

determining the occurrence frequency duty ratio of the maneuvering flight work envelope points, determining the work envelope area and the frequency of the maneuvering overload occurrence, and distributing the frequency of the maneuvering overload occurrence to the work envelope points according to the amplitude value to realize the matching of the maneuvering overload and the occurrence frequency thereof with the engine work envelope points;

and comparing the obtained maneuvering overload coefficient spectrum with a first type of construction basis, analyzing the rationality of the usage, and applying the maneuvering overload coefficient spectrum to the design and test of a new model of a cross-generation research.

Further, the process for determining the demand analysis and key characteristics of the maneuvering flight load spectrum of the cross-generation new-research model comprises the following steps:

identifying stakeholders and third-party specialists from the perspective of developing the cross-generation newly-developed aero-engine;

From the angles of a motor flight use scene and a use load, the needs and the expectations of stakes are acquired, the system positioning of a development object, the combat use scene, the use task, the required engine core capability and key indexes are analyzed, and key characteristics and construction points of a motor overload spectrum of a new cross-generation development type are defined.

Further, the first type of construction basis includes:

the method comprises the steps of selecting engines with motor overload amplitude values or using frequency and design requirements of the assembled aircraft, structural fatigue design load data, test load data, outfield use load statistical results and typical task profiles of the same type of engines according to various aircraft or general specifications of the engines and design and use data of the same type of active machine types in the past;

the element integrity analysis process of the first build basis includes element analysis of two aspects, the element analysis of the first aspect including:

1) Checking a forming method and a technical path of the construction basis, and judging the credibility of the construction basis and assisting in characteristic analysis;

2) From the aspects of maneuvering conditions and aerodynamic conditions forming a maneuvering overload spectrum, the completeness of elements is analyzed, and the meaning of the elements is as follows: the method comprises the steps that necessary flight parameters are provided for physical processes of typical use scenes including starting/warming up, running, taking off, climbing, cruising, maneuvering tasks, returning, cooling/stopping and the like, wherein the flight parameters comprise the stay time of task segments expressed by aerodynamic working conditions, maneuvering working conditions and aerodynamic working conditions, and the use times of each typical task section in a unit time period;

3) From the aspects of maneuver flight action characteristics, overload amplitude values or frequency, the construction basis elements capable of acquiring or partially acquiring the maneuver overload spectrum and the use degree of the elements capable of acquiring or partially acquiring the maneuver overload spectrum in reflecting the cross-generation new research model are respectively reviewed, and the construction basis elements incapable of acquiring the maneuver overload spectrum and the cause are respectively reviewed;

element analysis of the second aspect, comprising:

the typical task section in the first type of construction basis is enabled to meet two selected key points, wherein the key point I is as follows: the parameter entries of the typical task profile allow for incomplete situations to exist, but contain 6 classes of building elements: using mixing, altitude, mach number, engine operating conditions, dwell time, maneuver overload;

the key point is as follows: the same type of engine type simultaneously meets the requirement of aviation turbofan or turbojet engine with equivalent bypass ratio, and the selected engine displacement difference is as small as possible with the target engine type for constructing the maneuvering overload spectrum.

Further, collecting the second type of construction basis, and performing the element integrity analysis process of the second construction basis includes:

selecting data parameters describing the process of a typical maneuvering flight task from design, test and flight use data of the same type and the same type of tasks according to key characteristics and determination basis thereof, wherein the data parameters comprise flight altitude, mach number, engine working state or throttle lever angle, and longitudinal, transverse and normal maneuvering overload amplitude values; the similar engine type is similar to a motor overload spectrum construction target engine type or an aircraft assembled with the engine type;

The process of determining the motorized overload range of the second class of build basis comprises:

and selecting a typical flight action set similar to the task characteristics of the cross-generation new research machine type according to the given key characteristics and the construction basis element analysis results, and extracting the typical characteristics of the maneuver flight action to obtain a corresponding maneuver overload range.

Further, the normal maneuvering overload lower limit selects the minimum value of the positive and negative overload absolute values, and the normal maneuvering overload upper limit selects the maximum value of the positive and negative overload absolute values.

Furthermore, the small overload is a normal overload range with slight influence on the service life of the bearing structure of the engine, and the upper limit is 2g or less and Nz or less than 3g;

the middle overload is a normal overload range which has influence on the service life of a bearing structure of the engine but is not too large, and the upper limit is 6g less than or equal to Nz less than 7g;

the large overload is a normal overload range which has great influence on the service life of a bearing structure of the engine, and the lower limit is 6g less than or equal to Nz less than 7g.

Further, the process of determining the sum of the frequencies of the normal overload and the large overload includes:

if the design usage is similar to the construction basis of the new generation of the machine, the new generation of the machine is used as the total normal overload frequency with the amplitude above the medium amplitude according to the principle that the design usage is relatively similar;

If the design usage does not have a construction basis similar to that of the cross-generation new grinder, selecting the construction basis with the design usage in the prior art as the total normal overload frequency with the amplitude above the medium amplitude of the cross-generation new grinder, wherein the motor overload frequency is the largest;

if the existing construction basis does not contain the construction basis of the design usage, the maximum maneuvering overload frequency is selected from the general specification construction basis item and used as the total normal overload frequency with the amplitude above the medium amplitude of the cross-generation new grinder type.

Further, the process of determining the normal large overload frequency distribution includes:

according to the determined large overload range and the principle of similar design usage, evaluating the similarity and rationality of each construction according to the design usage, and determining the large overload frequency distribution of the cross-generation new research model;

the process of determining the normal mid-load frequency distribution:

according to the determined medium overload range and the principle of similar design usage, evaluating the similarity and rationality of each construction according to the design usage, and determining the medium overload frequency distribution of the new research model;

the process of determining the normal small overload frequency distribution:

according to the determined small overload range and the principle of similar design usage, evaluating the similarity and rationality of each construction according to the design usage, and determining the small overload frequency distribution of the cross-generation new research model;

If the design usage does not have a construction basis similar to that of the cross-generation new grinder, selecting the construction basis with the design usage in the prior art as the total normal small overload frequency of the cross-generation new grinder, wherein the motor overload frequency is the largest;

if the existing construction basis does not contain the design usage, the largest maneuvering overload frequency is selected as the total amount of normal small overload frequency of the cross-generation new grinder type in the general specification construction basis item.

Further, the process of determining the area and frequency of the work envelope where the motor overload occurs includes:

for the engine with a small bypass ratio, according to three task types, respectively constructing engine work envelope points where motor overload occurs, wherein the engine work envelope points are used for expressing the engine and a platform assembled with the engine to execute the conventional motor action pattern and the characteristic motor action pattern described in the step 1;

wherein, the first class of maneuver flight work envelope points corresponding to the first task type are: selecting a subsonic cruise point designated by a user side in a range of a height of more than or equal to 10 kilometers and less than 13 kilometers and a Mach number of more than or equal to 0.6 and less than 1.0 in a development requirement file provided by the user side, wherein the engine working state is a cruise state;

The second class of maneuvering flight work envelope points corresponding to the second task type are as follows: the height is less than 10 km, mach number is less than 1.0, the working state of the engine is any working state above the slow vehicle state, 1-2 working envelope points with the longest residence time are selected, wherein when the second envelope point with the longest working time is not less than 20% of the longest envelope point with the longest working time, 2 envelope points with the longest working time are selected as second class maneuver flight working envelope points; otherwise, selecting 1 envelope point with the longest working time as a second class maneuver flight working envelope point; if the second class of maneuver flight envelope points are 2, the sum of maneuver overload frequency duty ratios of the amplitude ranges of the second class of maneuver flight envelope points is distributed to the two envelope points according to the relative proportion of the specified working time distribution.

The third class of maneuver flight work envelope points corresponding to the third task type are: outside the working envelope area with the height less than 10 km and the Mach number less than 1.0, the working state of the engine is the middle and above working state;

according to the determined key characteristics of the maneuvering flight task of the novel engine, selecting a working envelope point serving as an engine key performance assessment index from a development requirement file provided by a user side according to the following two conditions:

Case 1: if the following three types of work envelope areas all have performance examination points which are designated as key indexes by a user side and are matched with the key characteristics of the maneuvering flight task of the novel engine determined in the step 1, 1-2 work envelope points are selected in each area, the selected number is determined according to the number of designated points of the user side, and if more than 2 points are designated by the user side, 2 points are selected:

characteristic task work envelope area i): a height of less than 10 km and a Mach number of greater than or equal to 1.0;

characteristic task work envelope area ii): the height is greater than or equal to 10 km, and the Mach number is greater than or equal to 1.0;

characteristic task work envelope area iii): the height is greater than or equal to 10 km and the Mach number is less than 1.0.

The cumulative operating time in the 3 envelope regions is counted as a relative proportion of the frequency of occurrence of the maneuver overload in the 3 envelope regions, taking into account the frequency of use of the representative task profile shown as 0, according to all the specified representative task profiles.

Case 2: if the three working envelope areas do not contain engine performance check points which are designated as key performance indexes by a user side or have the points which are not matched with key characteristics of the maneuvering flight task of the novel engine determined in the step 1, a maneuvering overload typical envelope point is not selected in the corresponding envelope area;

If the third class of maneuver flight envelope points have 2, the sum of maneuver overload frequency duty ratios of the amplitude ranges of the third class of maneuver flight envelope points is distributed to the two envelope points according to the relative proportion of the specified working time distribution.

Further, the process of distributing the occurrence frequency of the maneuvering overload to the working envelope point according to the amplitude comprises the following steps:

according to the dividing mode and the occurrence frequency proportion distribution of three types of maneuvering flight work envelope points, aiming at the dividing of the overload ranges of small overload, medium overload and large overload, the following operations are respectively carried out:

the maneuver overload range is the frequency proportion of the large overload maneuver overload: the occurrence frequency of the large overload motor overload amplitude is a specified value PCD, and the range of the PCD is more than or equal to 5% and less than or equal to 15%;

the maneuver overload range is the frequency proportion of the medium overload maneuver overload: the occurrence frequency of the medium overload motor overload amplitude is a specified value PCZ, and the range of the occurrence frequency is 35 percent or more and 45 percent or less;

the maneuver overload range is the frequency proportion of the maneuver overload of the small overload class: the occurrence frequency of the small overload motor overload amplitude is a specified value 'PCX', and the range of the PCX is more than or equal to 45% and less than or equal to 55%;

wherein, for the range of the large overload motor overload, according to the formula (MX)/(MX+1) =PCDD, determining the occurrence frequency of the motor overload amplitude, namely the ratio of the occurrence frequency of the rear term to the occurrence frequency of the front term is a specified value PCDD, and the range of the PCDD is more than or equal to 0.1 and less than or equal to 0.8;

For the range of the middle overload motor overload, determining the occurrence frequency of the motor overload amplitude according to the formula (MX)/(MX+1) =PCDD, wherein the occurrence frequency ratio of the rear term to the front term is a specified value PCDD, and the range of the PCDD is more than or equal to 0.1 and less than or equal to 0.8.

The method takes demand analysis as a starting point, is based on cross-generation new-research model design usage analysis, collects, analyzes, absorbs and integrates various existing limitation data conditions, and further constructs a method for obtaining the maneuvering overload spectrum, so that the problem that the maneuvering overload spectrum of the aeroengine has no direct design input, and the maneuvering overload spectrum cannot be directly obtained by using data statistics of outfield usage due to large difference of active model is solved, and basis is provided for the life design and test of an important bearing structure of the engine; due to the close fit of the cross-generation model design usage, the construction method can more accurately predict the maneuvering overload spectrum of the engine after service, ensure the design service life and not improve the development difficulty.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.

FIG. 1 is a flow chart of a load spectrum construction method of the present application.

Detailed Description

In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

In order to overcome the problems in the prior art, the method for constructing the motor overload spectrum of the cross-generation new-research model is provided by analyzing the design usage of the new research and development motor based on the use scene, capturing the motor overload use requirement, collecting, analyzing and integrating the design and use data of the active machine type, taking the elements forming the motor overload spectrum as the reconstruction target, and solving the problems of restricting the technical capability and development progress of the product caused by input deletion.

As shown in FIG. 1, aiming at the problems that the motor overload spectrum of the aeroengine has no direct design input and the motor overload spectrum cannot be obtained directly by outfield use data statistics due to large difference of active service type usage, the application provides a motor overload spectrum construction method of the aeroturbofan engine with small bypass ratio, which is used for designing and testing the service life of a bearing structure and comprises the following operation steps:

1. Motorized load demand capture and build basis collection

Step 1: analyzing the requirements of the motor-driven flight load spectrum of the cross-generation new-research model and determining key characteristics:

from the perspective of developing an aircraft engine by new generation, the interest of a user side (including a user side and an airplane side) of the engine and the like are identified, and a third party expert with related research is identified.

From the angles of a motor flight use scene and a use load, a method and a concept of demand analysis are applied, including top-level demand analysis, investigation and study on similar machine types/competing objects at home and abroad, interviews and thematic conferences, the demands and expectations of interest-critical persons are acquired through related top-level demand files, standards/specifications (general specifications, airworthiness demands and the like), research reports, document data collection and the like, the system positioning of development objects, combat use scenes and use tasks are analyzed, the required engine core capacity and key indexes are determined, and key characteristics and construction points of a motor overload spectrum are defined.

For example, from the perspective of maneuvering load, in the use task scene required by development of a new research model of a certain cross generation, the use pattern comprises ultra-normal maneuvering, high overload and ocean-going voyage, and the target fight object is mainly a certain A-series aircraft/engine in domestic and foreign active service. According to the use scene, the requirement of independent combat capability is estimated to be high, the maneuvering characteristics are more drastic, the overload is large, the frequency is high, and the maneuvering load level is high. Thus, the capacity requirements placed on engines are that they can be used continuously without unacceptable structural damage under flight load conditions with significant X1 maneuver technical features.

Correspondingly, in the development requirements of the similar active machine types, the use patterns comprise diving, symmetrical pulling, steady/unsteady coiling and maximum gust/gust, potential fight objects are active B series airplanes/engines at home and abroad, the intensity of maneuver motions is common, the maneuver load level is basically equivalent to that of a common advanced teaching machine, the core capacity requirement of the engine is that the engine bears the load under the normal maneuver flight condition of the airplane, and the engine can work normally and has no structural damage.

According to comparison of engine usage patterns, potential fight objects and capability requirements, key features of the maneuvering overload spectrum of the novel cross-generation engine are defined as follows:

1) The maneuver amplitude is large;

2) The large motor is overloaded frequently;

3) The characteristic of certain overload of the super motor is reflected.

Step 2: collecting a first type of construction basis according to key characteristics of the dynamic overload spectrum of the new machine, and analyzing element integrity of the construction basis:

according to the key characteristics in the step 1, collecting design and use data of various aircraft/engine general specifications and the prior similar active machine types, selecting an engine with maneuvering overload amplitude or use frequency and design requirements, structural fatigue design load data, test load data and outfield use load statistical results of the aircraft assembled with the engine, and typical task profiles of the same machine types. Because the dynamic load exists along with the pneumatic/thermal load of the engine according to the actual use scene, the dynamic load and the dynamic load are indistinguishable, and the dynamic load can be used for the life design and test of parts after being matched with the pneumatic working conditions (flying height, mach number and engine working state) of the engine. Thus, the data collected should include information in both motorized overload and aerodynamic operating conditions.

For example, according to the characteristics of large maneuvering amplitude, more frequency of large maneuvering overload and certain super maneuvering overload, the design or use data related to maneuvering overload spectrums of special performance aircrafts, air unmanned aerial vehicles and advanced teaching machines are searched.

The first class of construction relies on elemental analysis that includes two aspects:

2.1 Element analysis of the first aspect, comprising the following three analysis items:

first aspect element analysis item 1: the forming method and the technical path of the construction basis are checked and cleared and are used for judging the credibility of the construction basis and assisting in characteristic analysis. For example, the typical task section (containing maneuver overload information) of a similar active engine is acquired by using flight parameter data and simulation analysis data according to the outfield of a series of aircraft/engines and through statistical analysis and other modes, the high reliability and the high completeness of each element of the typical task section can be obtained;

first aspect element analysis item 2: objective analysis of element completeness in terms of maneuvering conditions and aerodynamic conditions constituting a maneuvering overload spectrum, wherein the element means that necessary flight parameters are given for physical processes including typical use scenes such as starting/warming up, running, taking off, climbing, cruising, tasks (maneuvering), returning, cooling/stopping, and the like, and the essential flight parameters include aerodynamic conditions (height, mach number, engine working state/or accelerator lever angle/or engine thrust requirement), maneuvering conditions (longitudinal/transverse/normal overload at the center of gravity of the engine), residence time of task segments expressed by the aerodynamic conditions, and the number of times (or called use mixing) of each typical task profile in a unit time period, and whether the elements are complete, contain or lack thereof are evaluated;

First aspect element analysis item 3: the desirability and limitation of the construction basis are respectively reviewed in terms of maneuver characteristics and overload amplitude/frequency. From the perspective of applicability of the use method of the motorized load to the new research model of the cross generation, the advisable point means that which elements can adopt the message (or part of the message) as the construction basis of the motorized overload spectrum, and how much the elements can be adopted can reflect the use method of the new research model of the cross generation; the limitation means that which elements (or certain aspects of which elements) cannot be adopted as the basis for constructing the motorized overload spectrum, and which key elements are not suitable as the basis for determining the aspect due to the lack of the key elements.

The carding results according to the first class of constructions (first aspect element analysis) are listed in table 1.

TABLE 1 first class construction basis item element analysis (example)

2.2 Element analysis of the second aspect, for typical task profiles in the first class of build basis, two selected points need to be satisfied:

typical task profile selection gist 1:

in an ideal state, the parameter item and the format example of the "typical task profile" are shown in table 2, and the mixing parameter item and the format example are shown in table 3, but when the building basis is collected, the condition that the parameter item is incomplete is allowed exists. In order to construct a complete matching relationship between the maneuvering and aerodynamic load conditions, element completeness analysis is performed on each construction basis of table 1 according to the method shown in table 4 for later determining the matching relationship between the maneuvering condition and the aerodynamic condition, wherein the matching relationship comprises (6 types of) construction elements: using mixing, altitude, mach number, engine operating conditions, dwell time, maneuver overload;

Table 2 typical task profile parameter terms and format examples

Table 3 use of mixing of typical task profiles

TABLE 4 analysis of the completeness of the basis elements for matching maneuver to pneumatic loads (examples)

Typical task profile selection gist 2:

the "same model" needs to satisfy two conditions simultaneously:

condition 1: the aviation turbofan/turbojet engine with equivalent bypass ratio, for example, the bypass ratio of the engine of the motor overload spectrum construction target model is smaller than 1.0, and the construction basis is selected from the turbojet or turbofan engine design and test run data with the bypass ratio smaller than 1.0;

condition 2: in the existing data which can be collected, the engine generation difference and the target model of the motor overload spectrum to be built are selected as small as possible, for example, if the target model is the (X) th generation according to the international or domestic accepted standard, the typical task sections which can be collected are sequentially selected according to the priority order of the (X) th generation, the (X-0.5) th generation and the (X-1) th generation.

Step 3: the second type of construction is based on collection and element analysis:

according to the key characteristics and the determination basis in the step 1, data describing the typical maneuvering flight task process are selected from design, test and flight use data of the same type and the same type of tasks, and in an ideal state, parameter items comprise flight altitude, mach number, engine working state (or throttle lever angle) and longitudinal, transverse and normal maneuvering overload amplitude values, as shown in table 5. The second type of construction basis can comprise design, test or flight data of the (X) th generation fighter/engine, the (X-1) th generation fighter/engine and flight data of a coach machine and an unmanned plane/engine facing the similar tasks; "like task" refers to the task of performing the use of the scenario described in step a).

TABLE 5 flight parameter entries and format examples for typical maneuver

Step 4: construction of the second class is based on maneuver overload range determination

According to the key characteristics given in the step 1 and the analysis results of the basis items in the table 1, in the construction basis items in the table 1, a typical flight action set similar to the task characteristics of the cross-generation new research model is selected, the typical characteristics (physical meaning and the like) of the maneuver flight action are extracted, and the corresponding maneuver overload range is given, as shown in the table 6.

TABLE 6 exemplary flight maneuver overload Range (example)

2. Motorized overload coefficient spectrum construction

2.1, determining the corresponding relation of normal overload partition and three-way overload range

Step 5: determining normal overload range

According to the method shown in Table 7, aiming at the motor overload spectrum of the cross-generation new-research machine type, listing the normal motor overload range of each construction basis; and comparing and analyzing the maneuvering overload range of each construction basis according to the following two principles to determine a normal maneuvering overload range:

principle 1: selecting the minimum value of positive/negative overload absolute values from the normal overload lower limit;

principle 2: the normal overload upper limit is chosen to be the maximum of the positive/negative overload absolute values.

TABLE 7 method for determining normal maneuver overload range (example)

Step 6: determining a normal overload amplitude partitioning mode:

according to typical characteristics of maneuver motions in step 3 (table 5) and normal overload ranges in step 4 (table 6), the normal maneuver overload amplitude determined in step 5 is divided into (2-5) intervals, each interval gives maneuver motion characteristics and possible maneuver motion types, and according to the source of maneuver motion data, construction basis items are indicated for the following maneuver overload spectrum construction flow, as shown in table 8.

Table 8 normal overload amplitude Range division, physical meaning and construction basis (example)

Step 7: three-way overload amplitude range correspondence determination

And (3) according to the matching result of the step (6) and the corresponding relation shown in the table (8), listing the longitudinal/transverse maneuvering overload range according to each construction basis, as shown in the table (9).

TABLE 9 correspondence of longitudinal/lateral overload to normal overload amplitude ranges (example)

2.2 Normal maneuver overload coefficient Spectrum construction

Step 8:3, dividing normal overload amplitude values in a large category:

for the matching result in the step 6 and the normal overload amplitude range shown in table 8, according to the corresponding physical meaning, the normal maneuver overload range is classified into 3 major categories according to the influence degree of the normal overload amplitude on the service life of the bearing structure: "small overload", "medium overload", "large overload". The bearing structure comprises, but is not limited to, a casing in which the main bearing of the engine is located and a casing in which the mounting joint is located.

The basic principle of determining the upper limit and the lower limit of the normal overload range of 3 categories is as follows:

principle 1: "small overload" refers to a normal overload range that affects the life of the engine load carrying structure slightly, with an upper limit of typically 2 g.ltoreq.Nz < 3g. For example, "range 1" and "range 2" in table 8;

principle 2: "medium overload" refers to a normal overload range that has an impact on the life of the engine load carrying structure, but is not too large, with an upper limit of typically 6 g.ltoreq.Nz < 7g. For example, "range 3" in table 8;

principle 3: "Large overload" refers to a normal overload range that has a significant impact on the life of the engine load carrying structure, with a lower limit of typically 6 g.ltoreq.Nz < 7g. For example, "range 4" in table 8.

In the following steps, the occurrence frequency of each normal overload range in table 8 is determined according to the sequence of large overload, medium overload and small overload in consideration of the contribution degree of the damage to the low cycle fatigue life of the engine load bearing structure.

Step 9: the sum of the frequencies of normal medium overload and large overload is determined:

as shown in table 10, the frequency of maneuver overload according to each construction basis is analyzed, and the frequency of maneuver overload amplitude above normal medium amplitude is determined according to the following three conditions;

case 1: if the construction basis that the design usage is similar to that of the cross-generation new research model exists, according to the principle that the design usage is relatively similar, as the total normal overload frequency with the above medium amplitude value of the cross-generation new grinder type. Wherein, the design usage refers to the key characteristics and the determination basis in the step 1;

Case 2: if the design usage does not have a construction basis similar to that of the cross-generation new grinder, selecting the construction basis with the design usage in the prior art as the total normal overload frequency with the amplitude above the medium amplitude of the cross-generation new grinder, wherein the motor overload frequency is the largest;

case 3: if the existing construction basis does not contain the construction basis of the design usage, the maximum maneuvering overload frequency is selected from the general specification construction basis item and used as the total normal overload frequency with the amplitude above the medium amplitude of the cross-generation new grinder type.

Table 10 method for determining sum of frequencies of overload and large overload in normal direction (example)

Step 10: normal large carrier frequency sub-distribution determination:

and (3) evaluating the similarity and rationality of each construction of the table 1 according to the design usage according to the principle that the design usage is similar, namely, the key characteristics and the determination basis in the step (1) are taken as judgment criteria, and determining the large carrier frequency sub-distribution of the cross-generation new research model. As shown in table 11, the frequency distribution of "according to 3" large overload is selected as the frequency distribution of large carrier frequency of the new research model of cross generation according to the similarity and rationality of design usage. The "frequency ratio" is used for measuring the similarity of the design usage, and the "frequency ratio" is similar, i.e. the design usage is similar.

Table 11 normal large carrier frequency sub-distribution determination

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Note that: and (N) is the maximum normal overload amplitude.

Step 11: and (3) normal medium-load frequency distribution determination:

and (3) evaluating the similarity and rationality of each construction basis design usage of the table 1 according to the principle that the design usage is similar in the range of the medium overload determined in the step 8, namely taking the key characteristics and the determination basis of the key characteristics in the step 1 as judgment criteria, and selecting the medium overload frequency distribution determination basis of the cross-generation new research machine type as shown in a table 12. The "frequency ratio" is used for measuring the similarity of the design usage, and the "frequency ratio" is similar, i.e. the design usage is similar.

The selection of the reference for the overload frequency distribution in Table 12 (example)

The frequency ratio was kept substantially unchanged and the selected build basis was adjusted to ensure that the sum of the medium overload, large carrier frequency passes met the determination of table 10, as shown in table 13.

Overload frequency distribution determination (example) in Table 13

Step 12: normal small overload frequency distribution determination:

analyzing the maneuvering overload frequency according to the construction basis of each item, determining the frequency of the normal small overload amplitude value,

case 1: the similarity and rationality of each construction basis design usage of the table 1 are evaluated according to the principle that the design usage is similar in the range of the small overload determined in the step 8, namely, the key characteristics and the determination basis thereof in the step 1 are taken as judgment criteria, and the small overload frequency distribution determination basis of the new research model of the cross generation is selected as shown in a table 14;

Table 14 method (example) for determining small-amplitude normal overload frequency

Case 2: if the design usage does not have a construction basis similar to that of the cross-generation new grinder, selecting the construction basis with the design usage in the prior art as the total normal small overload frequency of the cross-generation new grinder, wherein the motor overload frequency is the largest;

case 3: if the existing construction basis does not contain the design usage, the largest maneuvering overload frequency is selected as the total amount of normal small overload frequency of the cross-generation new grinder type in the general specification construction basis item.

Since the normal small overload amplitude is small, the service life of the load bearing structure of the engine is slightly influenced, in the maneuvering overload spectrum, different amplitudes are not set for normal overload in the range, and all clusters are clustered to one amplitude, for example, if the normal small overload upper limit is determined in the step 8 (nz=3g), the overload frequencies of nz=1g, 2g and 3g are all expressed in the maneuvering overload spectrum (nz=3g).

2.3, motorized overload coefficient Spectrum Synthesis

Step 13: motorized overload coefficient spectrum synthesis:

the corresponding relation between the longitudinal/transverse overload and the normal overload amplitude range of the table 9, the normal large carrier frequency distribution of the table 11, the medium overload frequency distribution of the table 13 and the small normal overload frequency of the table 14 are summarized, and the maneuvering overload coefficient spectrum is constructed as shown in the table 15.

Motorized overload coefficient spectrum validation: and (3) according to the key characteristics and the determination basis thereof in the step (1) and the construction basis of the table (1), comparing and analyzing with the maneuvering overload coefficient spectrum shown in the table (15) to confirm rationality.

TABLE 15 motorized overload coefficient spectra (example)

3. Motor overload and matching of occurrence frequency of motor overload and engine work envelope point

3.1, determining the area and frequency of the work envelope where the motor overload occurs

Step 14: for a small bypass ratio engine (the bypass ratio is smaller than 1.0), respectively constructing engine work envelope points for occurrence of motor overload according to three task types, and expressing the engine and a matched platform thereof to execute the conventional motor action pattern and the characteristic motor action pattern in the step 1, wherein the specific selection modes comprise:

task type 1: first kind of maneuvering flight work envelope point

In a development requirement file provided by a user side, selecting a subsonic cruise point designated by the user side within the range of the height of more than or equal to 10 kilometers and less than 13 kilometers and the Mach number of more than or equal to 0.6 and less than 1.0, wherein the engine working state is a cruise state. For example, the subsonic cruise points explicitly indicated in the development requirements on the part of the user are shown in table 2 (height 12 km, mach number 0.8, cruise state), and typically only one such point.

And (3) relative to the total amount of the maneuver overload frequency with Nz more than or equal to 3g shown in the table 15 in the step 11, the sum of the maneuver overload frequency duty ratios of the amplitude ranges of the maneuver flight work envelope points of the first class is a specified value PC1, and the range is more than or equal to 1% and less than or equal to 10% of PC 1.

Task type 2: second class maneuver flight work envelope point

In all specified typical task profiles shown in a table 2 of a first element analysis 2 in the step 2, taking the use mixing of the typical task profiles shown in the table 3 into consideration, selecting (1-2) working envelope points with the longest residence time (typical working conditions, distinguishing the middle or maximum state), wherein when the envelope point with the second working time is not less than (20%) of the envelope point with the longest working time, selecting (2) envelope points with the longest working time as second class maneuvering flight working envelope points; otherwise, selecting (1) envelope points with the longest working time as second class maneuvering flight envelope points. As shown in table 16, X20, X29 were chosen as the second class maneuver flight envelope points.

Table 16 second class maneuver flight envelope point selection method (example)

And (3) relative to the total amount of the maneuver overload frequency with Nz more than or equal to 3g shown in the table 15 in the step 11, the sum of the maneuver overload frequency duty ratios of the amplitude ranges of the maneuver flight work envelope points of the second class is a specified value PC2, and the range is more than or equal to 45% and less than or equal to 55% of PC 2.

If there are 2 envelope points of the second class of maneuver, PC2 is assigned to both envelope points in the relative proportion of its prescribed operating time assignment.

Task type 3: third class maneuver flight work envelope point

Outside the working envelope area with the height less than 10 km and the Mach number less than 1.0, the engine working state is the middle and above working state, and the sum of the frequency occupation ratios of the maneuvering overload frequency of each amplitude range of the third maneuvering flight working envelope point is a specified value PC3, and the range of the frequency occupation ratio is more than or equal to 35% and less than or equal to 50% relative to the total maneuvering overload frequency of Nz more than or equal to 3g shown in the table 15 in the step 11.

According to the key characteristics of the novel engine maneuvering flight task determined in the step 1, selecting a working envelope point serving as an engine key performance assessment index from a development requirement file provided by a user side according to the following two conditions:

case 1: if the following three types of work envelope areas all have performance check points which are designated as key indexes by a user side and are matched with the key characteristics of the maneuvering flight task of the novel engine determined in the step 1, 1-2 work envelope points are selected in each area, the selected number is determined according to the number of designated points of the user side, if the number of designated points of the user side is more than 2, 2 points are selected according to the method shown in the task type 2 and the table 16,

In accordance with the "second aspect" of step 2, all of the prescribed exemplary task profiles shown in table 2, the cumulative operating time in the above-described 3 envelope regions is counted as a relative proportion of the occurrence of the maneuver overload frequency in the 3 envelope regions, taking into account the use mixing of the exemplary task profile shown in 0.

Case 2: if the three working envelope areas do not contain engine performance check points designated as key performance indexes by a user side or have the points which are not matched with key characteristics of the maneuvering flight task of the novel engine determined in the step 1, the maneuvering overload typical envelope points are not selected in the corresponding envelope areas.

If there are 2 envelope points of the third class of maneuver, then "PC3" is assigned to both envelope points in the relative proportion of its prescribed operating time assignment.

The frequency of occurrence of the maneuver flight envelope points is determined by a process shown as 0.

TABLE 17 determination of frequency of occurrence of maneuver flight envelope points (example)

3.2, distributing the occurrence frequency of the maneuvering overload to a working envelope point according to the amplitude value, wherein the process comprises the following steps:

step 15: according to the dividing mode and the occurrence frequency proportion distribution of three types of maneuvering flight work envelope points in the step 14, aiming at the dividing of the large overload ranges of small overload, medium overload and large overload 3 determined in the step 8, the following operations are respectively carried out:

the maneuver overload range is the frequency proportion of the maneuver overload of the large overload class: compared with the occurrence frequency of overload in the area of the three maneuvering flight work envelope lines determined in the step 14, the occurrence frequency of the maneuvering overload amplitude of the large overload is a specified value PCD, and the range of the occurrence frequency is more than or equal to 5% and less than or equal to 15%.

Within the "large overload" class maneuver overload range determined for step 8, according to the formula "(M _X )/(M _X +1) =pcdd ", and the occurrence frequency on the amplitude of the motor overload, that is, the ratio of the occurrence frequency of the latter term to the former term, is determined to be a specified value PCDD, the range of which is 0.1-0.8.

The maneuver overload range is the frequency proportion of the maneuver overload of the medium overload type: and (2) relative to the occurrence frequency of the overload in the area of the three maneuvering flight work envelope lines determined in the step (14), the occurrence frequency of the maneuvering overload amplitude of the medium overload class is a specified value PCZ, and the range of the PCZ is more than or equal to 35% and less than or equal to 45%.

Within the "medium overload" class maneuver overload range determined for step 8, according to the formula "(M _X )/(M _X +1) =pcdd ", and the occurrence frequency on the amplitude of the motor overload, that is, the ratio of the occurrence frequency of the latter term to the former term, is determined as a specified value" PCDD ", which is in the range of 0.1+.pcdd+.0.8.

The maneuver overload range is the frequency proportion of maneuver overload occurrence of the small overload class: and (2) relative to the occurrence frequency of the overload in the area of the three maneuvering flight work envelope lines determined in the step (14), the occurrence frequency of the maneuvering overload amplitude of the small overload class is a specified value 'PCX', and the range of the PCX is more than or equal to 45% and less than or equal to 55%.

The frequency of occurrence of motor overload is distributed to the points of the work envelope by amplitude as shown in table 19.

TABLE 19 course of frequency of occurrence of motor overload to points of working envelope by amplitude (example)

4. Construction result rationality validation

Step 16: the final format of the motor overload spectrum is shown in table 19, and the final format is compared with the construction basis in table 1, the rationality of the analysis usage is improved, the use requirement is met, and the final format is agreed with the user side and then is applied to the design and test of a new research model of the cross-generation type.

TABLE 19 motorized overload spectrum construction results (example)

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The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft engine maneuver overload spectrum construction method for constructing maneuver load spectrum of a cross-generation new research model is characterized by comprising the following steps:

determining key characteristics of a maneuvering flight load spectrum of the cross-generation new-grinder type by using a demand analysis method, collecting a first type construction basis and a second type construction basis according to the key characteristics of the maneuvering flight load spectrum of the cross-generation new-grinder type, and performing element integrity analysis of the first construction basis and the second construction basis to determine a maneuvering overload range of the second type construction basis;

According to the influence degree of the normal overload amplitude on the service life of the bearing structure of the engine, the normal maneuvering overload range is classified into three categories, including small overload, medium overload and large overload; determining the sum of frequencies of normal medium overload and large overload and the frequency distribution of normal large overload, medium overload and small overload, and synthesizing the corresponding relation between the longitudinal or transverse overload and the normal overload amplitude range and the frequency distribution of normal large overload, medium overload and small overload to obtain a maneuvering overload coefficient spectrum;

and comparing the obtained maneuvering overload coefficient spectrum with a first type of construction basis, analyzing the rationality of the usage, and confirming that the usage requirement is met, so that the maneuvering overload coefficient spectrum is applied to the design and test of the low cycle fatigue life of the load-carrying structure of the cross-generation new-research engine.

2. The aircraft engine maneuver load spectrum building method as defined in claim 1, wherein determining key features of the maneuver load spectrum of the cross-generation new-development machine using the demand analysis method comprises:

from the angles of a motor flight use scene and a use load, the needs and the expectations of stakes are captured, the system positioning of a development object, the combat use scene, the use task, the required engine core capability and key indexes are analyzed, and key characteristics and construction points of a motor overload spectrum of a new cross-generation development type are defined.

3. The method for constructing an aeroengine maneuver overload spectrum as claimed in claim 1 wherein the first class of construction basis comprises:

3) From the aspects of maneuver flight action characteristics, overload amplitude values or frequency, the construction basis elements capable of acquiring the signals or part of the signals as maneuver overload spectrums, the degree of reflecting the usage method of the new generation machine type by the elements capable of acquiring the signals or part of the signals, and the elements and the causes incapable of acquiring the signals as the construction basis of the maneuver overload spectrums are respectively reviewed;

element analysis of the second aspect, comprising:

the typical task profile in the first class of construction basis is made to satisfy two selected gist, wherein,

the key point is as follows: evaluating element integrity of a typical mission profile according to class 6 building elements, including using mixing, altitude, mach number, engine operating conditions, dwell time, maneuver overload, said class 6 building elements allowing for incomplete conditions to exist;

The key point is as follows: the meaning of the same type of engine type is that aviation turbofan or turbojet engine with equivalent bypass ratio is met at the same time, and the selected engine displacement difference is as small as possible with the target engine type of the maneuvering overload spectrum to be constructed.

4. The method for constructing an engine maneuver overload spectrum for an aircraft engine as claimed in claim 1, wherein the process of collecting the second type of construction basis and performing the element integrity analysis of the second construction basis comprises:

selecting data parameters describing the process of a typical maneuvering flight task from design, test and flight use data of the same type and the same type of tasks according to key characteristics and determination basis thereof, wherein the data parameter items comprise flight altitude, mach number, engine working state or throttle lever angle, and longitudinal, transverse and normal maneuvering overload amplitude values; the similar engine type is similar to a motor overload spectrum construction target engine type or an aircraft assembled with the engine type;

and selecting a typical flight action set similar to the task characteristics of the cross-generation new research machine type according to the given key characteristics and the construction basis element analysis results, extracting the typical characteristics of the maneuvering flight action, and obtaining a corresponding maneuvering overload range.

5. The method for constructing an aircraft engine maneuver overload spectrum as claimed in claim 1, wherein the lower normal maneuver overload limit is chosen as the minimum of the absolute positive and negative overloads and the upper normal maneuver overload limit is chosen as the maximum of the absolute positive and negative overloads.

6. The method for constructing an engine-driven overload spectrum of an aircraft engine according to claim 1, wherein the small overload is a normal overload range with slight influence on the service life of a load-carrying structure of the engine, and the upper limit is 2g < Nz < 3g;

7. The method for constructing an aircraft engine maneuver overload spectrum as claimed in claim 1 wherein the process of determining the sum of the frequencies of normal medium overload and large overload comprises:

8. The method for constructing an aircraft engine maneuver overload spectrum as claimed in claim 1 wherein the process of determining the normal large overload frequency distribution comprises:

the process of determining the normal mid-load frequency distribution:

the process of determining the normal small overload frequency distribution:

if the construction basis of the design usage is similar to that of the cross-generation new grinder, evaluating the similarity and rationality of each construction basis of the design usage according to the principle of the design usage similarity and the principle of the design usage according to the determined small overload range, and determining the small overload frequency distribution of the cross-generation new grinder;

9. The method for constructing an aircraft engine maneuver overload spectrum as claimed in claim 1, wherein the process of determining the area and frequency of the operating envelope in which the maneuver overload occurs comprises:

for the engine with a small bypass ratio, according to three task types, respectively constructing engine work envelope points where motor overload occurs, wherein the engine work envelope points are used for expressing a conventional motor action pattern and a characteristic motor action pattern executed by the engine and an assembled platform of the engine;

The second class of maneuvering flight work envelope points corresponding to the second task type are as follows: the height is less than 10 km, mach number is less than 1.0, the working state of the engine is any working state above the slow vehicle state, 1-2 working envelope points with the longest residence time are selected, wherein when the second envelope point with the longest working time is not less than 20% of the longest envelope point with the longest working time, 2 envelope points with the longest working time are selected as second class maneuver flight working envelope points; otherwise, selecting 1 envelope point with the longest working time as a second class maneuver flight working envelope point; if the number of the second class maneuver flight envelope points is 2, distributing the sum of maneuver overload frequency duty ratios of the amplitude ranges of the second class maneuver flight envelope points to the two envelope points according to the relative proportion of the specified working time distribution;

Case 1: if the following three types of work envelope areas all have performance examination points which are designated as key indexes by a user side and are matched with the determined key characteristics of the maneuvering flight task of the novel engine, 1-2 work envelope points are selected in each area, the selected number is determined according to the number of designated points of the user side, and if more than 2 points are designated by the user side, 2 points are selected:

characteristic task work envelope area iii): the height is more than or equal to 10 km, and the Mach number is less than 1.0;

counting the cumulative operating time in the 3 envelope regions as the relative proportion of the occurrence of the maneuver overload frequency between the 3 envelope regions, taking into account the use mixing of the representative task profile shown in the element analysis of the second aspect, according to all the defined representative task profiles;

10. The method for constructing a maneuvering overload spectrum of an aeroengine according to claim 1, wherein the process of distributing the occurrence frequency of the maneuvering overload to the working envelope point according to the amplitude is as follows:

Wherein, within the range of the motor overload of the large overload class, the motor overload is controlled according to the formula (M _X )/(M _X +1) =PCDD, determining the occurrence frequency of the motor overload amplitude, namely the ratio of the occurrence frequency of the last item to the occurrence frequency of the first item is a specified value PCDD, and the range of the PCDD is more than or equal to 0.1 and less than or equal to 0.8;

for the range of the motor overload of the medium overload class, the motor overload range is calculated according to the formula (M _X )/(M _X +1) =pcdd, and the occurrence frequency of the motor overload amplitude, that is, the ratio of the occurrence frequency of the last term to the occurrence frequency of the preceding term, is determined to be a specified value PCDD, and the range of the PCDD is equal to or more than 0.1 and equal to or less than 0.8.