CN110083902A - A kind of temperature distortion map mimetic design method based on discrete series - Google Patents
A kind of temperature distortion map mimetic design method based on discrete series Download PDFInfo
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Abstract
A kind of temperature distortion map mimetic design method based on discrete series.Determine speed of incoming flow and upstream distortion the distance between section and downstream map section；To the arranged distribution number of nozzle, and the hot-fluid composite sequence of each nozzle is set as vector α；The target map section in downstream is divided into the unit of magnitude N, by the minute cells got using horizontal direction as zero degree line, minute cells sequence is carried out outward, is denoted as map column vector β；Column vector Q is constructed respectively1..., Qi..., QM, measure the temperature distortion map in downstream；Generalized inverse matrix B is taken to matrix A, determines the distribution of hot-fluid；According to vector α, obtain the state of each nozzle in upstream, specific temperature distortion pattern is realized by adjusting hot-fluid injection intensity, and obtained result provides data supporting for the temperature distortion probed under real working condition, therefore this mimetic design method is to use matrix A and column vector β reverse column vector α.
Description
Technical field
The present invention relates to the aerodynamic stability assessment technologies of aero-engine, push away more particularly, to according to temperature distortion map
Calculate a kind of temperature distortion map mimetic design method based on discrete series of heat source distribution situation.
Background technique
The aerodynamic stability of aero-engine is to assess the important indicator of engine performance, it is required that engine is in addition to having
Other than the superior function of key Design state, the interference for dropping steady factor can be resisted in entire flight envelope, guaranteed enough
Available stability margin (Nanjing [1] Zhao Yunsheng aero-engine aerodynamic stability analysis system research [D] aerospace is big
It learns, 2013).However during air formation flight, MISSILE LAUNCHING etc., engine intake just inevitably sucks hot-fluid, heat
The sucking of stream will bring apparent temperature distortion to engine intake, serious temperature distortion will lead to engine enter it is unstable
Working condition will be of great significance to the deep understanding of temperature distortion problem to the development and design of the following aero-engine.
In view of the great influence that temperature distortion works to engine stabilizer, the U.S., Britain, China, Russia etc. mainly navigate
Empty big country has carried out mechanistic, systematic research to temperature distortion, and has formulated corresponding temperature distortion generation and simulator
Design method ([2] Dai Bing, Ye Wei the United States, Russia Aeroengine Stability Contrast of Standard [J] aviation standardization and quality,
2009(02):44-48).A certain number of nozzles are mainly arranged in existing temperature distortion in the intake channel, carry out at nozzle
Ignition or hot-fluid injection pass through the heat flow rate per unit area of control nozzle to realize that the part of gas flow temperature increases to reality
The purpose of existing distortion measurement section map customization.Currently, specified temperature distortion map in order to obtain, Main is in engineering
On determining nozzle quantity and nozzle distributed basis, by way of numerical simulation or test, to the heat flow rate per unit area of nozzle
Combination is studied.Due to lacking the custom design method of temperature distortion map at present, in the fine of temperature distortion map
To expend a large amount of manpower and material resources in debugging, and it is long there are the lead time, design is complicated, test randomness is big the problems such as, therefore
Find one kind can be easily obtained Complex Temperature distortion pattern and map accuracy temperature distortion design method it is aobvious
It obtains very necessary.
Summary of the invention
The purpose of the present invention is intended to the deficiencies of for existing temperature distortion map method for accurately designing, according to temperature distortion figure
Spectrum calculates heat source distribution situation, provides a kind of temperature distortion map mimetic design method based on discrete series.
The present invention the following steps are included:
1) according to given measurement section temperature map distribution, speed of incoming flow and upstream distortion section and downstream map are determined
The distance between section；
2) nozzle quantity M is generated according to temperature and nozzle is distributed, serial number is carried out to the arranged distribution of nozzle, and will be each
The hot-fluid composite sequence of nozzle is set as vector α；
3) the target map section in downstream is divided into the unit of magnitude N, by the minute cells got with level
Direction is zero degree line, and one encloses progress minute cells sequence outward, and based on temperature distortion map by the way of interpolation
Temperature assignment is carried out to N number of unit, and is denoted as map column vector β；
4) column vector Q is constructed respectively1,…,Qi,…,QM, wherein QiIt is denoted as (q1,…,qi,…,qM)T, remove q1Be set as 1 it
Outside, other numerical value are set as 0, that is, indicate to be in maximum State of Thermal Liquid Based except i-th of nozzle, and other M-1 are in closed state,
Wherein, maximum State of Thermal Liquid Based is denoted as 1, and minimum thermal flux state is denoted as 0；
5) carry out i-th of nozzle respectively and be in maximum hot-fluid, the other M-1 numerical simulations or examination being in close state
Research is tested, the temperature distortion map in downstream is measured, and with reference to the number of step 3), obtains vector (a1i, a2i, a3i…aNi)T, always
Total M nozzle forms matrix
6) according to A α=β, generalized inverse matrix B is taken to matrix A, wherein BA=EM, EMFor M rank unit matrix, reverse hot-fluid
Distribution vector α, i.e. α=B β, so that it is determined that the distribution of hot-fluid, wherein maximum value 1, minimum value 0 in vector α；
7) according to resulting vector α, the state of each nozzle in upstream is obtained, i.e., is realized by adjusting hot-fluid injection intensity special
Determine temperature distortion map, obtained result provides data supporting for the temperature distortion probed under real working condition, therefore this mimetic design side
Method is to use matrix A and column vector β reverse column vector α.
The present invention can be analyzed by the construction and solution of vector and matrix, the hot-fluid discrete series distribution of middle and upper reaches
For vector α, downstream flow Temperature Distribution is vector β, and relationship between the two is matrix A, the building side of vector α, β and matrix A
Method is detailed in specific embodiment part.
The present invention can the more accurately mimetic design theoretical method in true flow field shown in reproducible temperature distortion pattern, i.e., with
Existing temperature distortion map is target, and under specific temperature nozzle arrangement state, reverse obtains being capable of forming shown in map
The heat flow rate per unit area of temperature distortion field is distributed, it is contemplated that and temperature distortion map generally provides under specific speed of incoming flow state, on
The distance between distortion generator and temperature distortion measurement section generally fixed value are swum, and the temperature in engineering generates nozzle number
Amount and nozzle distribution are general given, and the solution for carrying out upstream temperature distortion generator for temperature distortion map can be regarded as: to
Trip flowing temperature distribution is fixed, the relationship between upstream hot-fluid and downstream temperature distribution, the discrete sequence of the hot-fluid of reverse upstream are constructed
Column.
The present invention considers that the upstream section temperature in engineering generates nozzle quantity and nozzle distribution is general given, downstream temperature
Degree distortion spatial distribution, which mainly passes through, to be adjusted the heat flow rate per unit area of nozzle and is handled, by by the condition of nozzles of different heat flow rate per unit areas
Handle the correlation between discrete series, different spray nozzles then and can be regarded as the vector operation between different discrete series.Knot
The affecting laws that trip hot-fluid is distributed measured downstream section temperature are closed, different condition of nozzles discrete series, Ji Keshi are constructed
Existing upstream temperature distortion generator analyzes the positive affecting laws of downstream temperature distortion pattern.So-called mimetic design is then by
The temperature distortion map known finds the discrete series combination of upstream nozzle, to realize the design of temperature distortion simulator.
The present invention has technical effect following prominent:
The heat flux distribution under real working condition can be simulated using the present invention and obtains the higher temperature distortion figure of precision
Spectrum.Influence due to nozzle each in burning zone to thermometric face is quantified, and avoids test because a large amount of randomness is attempted
The waste of manpower and material resources caused by and, substantially reduces the test period.Meanwhile mimetic design method is only needed to set up to have and be mapped
The database of the matrix A of rule, can be quickly obtained corresponding heat flux distribution from different temperature distortion maps, compare
Reduce testing expense significantly in conventional method.
Detailed description of the invention
Fig. 1 is temperature distortion experimental rig diagrammatic top view.
Fig. 2 is a kind of distribution schematic diagram (M=21) of ignition burner in burning zone in Fig. 1 in test section.
Fig. 3 is a kind of distribution schematic diagram (N=40) in the thermometric face in test section downstream in Fig. 1.
Fig. 4 is a kind of temperature distortion map schematic diagram that the thermometric face in test section downstream in Fig. 1 is obtained by test simulation.
Label in figure are as follows: 1 indicate test section in burning zone, 2 indicate test sections in burning zone 1 in fuel pipe, 3
Indicate the mixing section in test section, 4 indicate the thermometric face in test section downstream, and 5 indicate the gas transmission in the burning zone 1 in test section
Pipe, 6 indicate the fixed link in the burning zone 1 in test section, and 7 indicate the air inlet of test section upstream, light a fire in 8 expression test sections
Nozzle throat area is to the distance in thermometric face, and 9 indicate ignition burner, and 10 indicate the temperature point in thermometric face, and 11 indicate that temperature is abnormal
Become the high temperature distorted region in map.
Specific embodiment
Following embodiment will the present invention is further illustrated in conjunction with attached drawing.
The embodiment of the present invention includes following steps:
1) according to given measurement section temperature map distribution, speed of incoming flow and upstream distortion section and downstream map are determined
The distance between section；
2) nozzle quantity M is generated according to temperature and nozzle is distributed, serial number is carried out to the arranged distribution of nozzle, and will be each
The hot-fluid composite sequence of nozzle is set as vector α；
3) the target map section in downstream is divided into the unit of magnitude N, by the minute cells got with level
Direction is zero degree line, and one encloses progress minute cells sequence outward, and based on temperature distortion map by the way of interpolation
Temperature assignment is carried out to N number of unit, and is denoted as map column vector β；
4) column vector Q is constructed respectively1,…,Qi,…,QM, wherein QiIt is denoted as (q1,…,qi,…,qM)T, remove q1Be set as 1 it
Outside, other numerical value are set as 0, that is, indicate to be in maximum State of Thermal Liquid Based except i-th of nozzle, and other M-1 are in closed state,
Wherein maximum State of Thermal Liquid Based is denoted as 1, and minimum thermal flux state is denoted as 0；
5) carry out i-th of nozzle respectively and be in maximum hot-fluid, the other M-1 numerical simulations or examination being in close state
Research is tested, the temperature distortion map in downstream is measured, and with reference to the number of step 3), obtains vector (a1i, a2i, a3i…aNi)T, always
Total M nozzle forms matrix
6) according to A α=β, generalized inverse matrix B is taken to matrix A, wherein BA=EM, EMFor M rank unit matrix, reverse hot-fluid
Distribution vector α, i.e. α=B β, so that it is determined that the distribution of hot-fluid, wherein maximum value 1, minimum value 0 in vector α；
7) according to resulting vector α, the state of each nozzle in upstream is obtained, i.e., is realized by adjusting hot-fluid injection intensity special
Determine temperature distortion map, obtained result provides data supporting for the temperature distortion probed under real working condition, therefore this mimetic design side
Method is to use matrix A and column vector β reverse column vector α.
Fig. 1 provides temperature distortion experimental rig diagrammatic top view, is substantially the same with traditional experiment device, and ignition burner 9 relies on
The fixed link 6 in burning zone 1 in test section is mutually stablized, and fuel pipe 2 and test in the burning zone 1 in test section
Section in burning zone 1 in appendix 5 and each nozzle communicate；The length of mixing section 3 in test section is ignition burner 9
The cross section distance 8 of ignition burner cross section to thermometric face into the test section in the thermometric face 4 in test section downstream.Mimetic design method
The anti-heat flux distribution released is mainly manifested on Fig. 2 ignition burner cross section, is adjusted according to the result vector α of mimetic design method
The ignition burner 9 in burning zone 1 in test section utilizes the temperature point in thermometric face on the thermometric face 4 in test section downstream
10 obtain data, obtain Fig. 4 temperature distortion simulation map after handling data, and it is compared with known temperature distortion map
Right, if degree of closeness is preferable, the heat flow field simulated can characterize true heat flow field.
Temperature distortion test section of the invention there are two main section, be respectively upstream ignition burner cross section and
The thermometric face in downstream.In practical operation, according to given temperature distortion map, the temperature of each unit is determined on thermometric face
Value, simulates heat flux distribution in real working condition further according to mimetic design method, specific as follows:
Definition: the combustion intensity of i-th of ignition burner is αi, obtaining heat flux distribution is vector α；It is each on the thermometric face of downstream
The temperature value obtained on measuring point is denoted as bj, all temperature values constitute map column vector β.
Assuming that heat flux distribution is α=(α at a certain moment1,α2,...,αi,…,αM)T, and some measuring point j should on thermometric face
The temperature at moment is influenced respectively by each nozzle for α based on the other factors in addition to hot-fluidj1,αj2,...,αji,…,αjM,
These values are measured from test, wherein need to only know influence of three ignition burners to downstream thermometric face on a certain axis, can be pushed away
Calculate the value for obtaining being left several nozzles.By the linear superposition theorem of data point it is found that point j under other factors by being influenced
For αj1+αj2+αji+…+αjM, each preceding combustion intensity α multiplied by each nozzle at this time of above formulaiIt can obtain moment point n temperature
Spend total impact effect bj, i.e. bj=α1*αj1+α2*αj2+αi*αji+…+αM*αjM.Therefore according to the thought and so on, can construct
Matrix A reflects that upstream heat source influences mapping principle to the temperature in downstream thermometric face:
And A α=β
According to A α=β, generalized inverse matrix B is taken to matrix A, wherein BA=EM, EMFor M rank unit matrix, therefore can be with reverse
Heat flux distribution vector α, i.e. α=B β, so that it is determined that the distribution of hot-fluid.
The waste of manpower and material resources caused by the invention avoids tests due to a large amount of randomness is attempted, substantially reduces examination
Test the period；Mimetic design method only needs to set up the database of the matrix A with mapping principle simultaneously, can be from different temperature
Distortion pattern, which sets out, is quickly obtained corresponding heat flux distribution, reduces testing expense significantly compared to conventional method.
As shown in figures 1-4, the present invention includes the burning zone 1 in test section, the fuel pipe in the burning zone 1 in test section
2, the mixing section 3 in test section, the thermometric face 4 in test section downstream, the appendix 5 in the burning zone 1 in test section, in test section
Burning zone 1 in fixed link 6, the air inlet 7 of test section upstream, distance of the ignition burner cross section to thermometric face in test section
8, ignition burner 9, the temperature point 10 in thermometric face, the high temperature distorted region 11 in temperature distortion map.
Firstly, according to the model of engine, determine ignition burner cross section to thermometric face distance 8.Then basis is started
The working condition of machine carries out serial number to it according to the arranged distribution of 12 ignition burners 9, and calculates each ignition burner 9
Combustion intensity function curve.
Coding rule is as follows:
On the circular section at heat source, using the center of circle as vertex, a ray is drawn horizontally to the right, this ray is set as horizontal
Reference line, i.e. 0 ° of line, and rotation is positive counterclockwise.By horizontal datum along rotating in the forward direction and piece seeks ignition burner, wherein right
In the ignition burner 9 on same ray, radial number consecutively outside from the center of circle.According to above-mentioned numbering, by M fire-fightings
Mouth 9 successively sorts.
The combustion intensity of each ignition burner is obtained by adjusting gas transmission and fuel feeding, and theoretically maximum combustion intensity is set to
1, minimum value 0, remaining value obtains between 0~1.
The target map section in downstream is divided into the unit of magnitude N, by the minute cells got with level side
To for zero degree line, one encloses and carries out minute cells sequence outward, and based on temperature distortion map by the way of interpolation to N
A unit carries out temperature assignment, and is denoted as map column vector β.
It controls i-th of ignition burner operation, is left M-1 ignition burner and closes, i.e. Qi=(q1,…,qi,…,qM)T,
In, qiIt is set as 1, other numerical value are set as 0, and maximum State of Thermal Liquid Based is denoted as 1, and minimum thermal flux state is denoted as 0.Carry out respectively
I ignition burner is in maximum hot-fluid, the other M-1 numerical simulations or experimental study being in close state, and measures downstream
Temperature distortion map, and with reference to above-mentioned downstream targets map section coding rule, obtain vector (α1i,α2i,...,
α3i,…,αNi)T.M ignition burner 9 can form matrix in total
According to A α=β, generalized inverse matrix B is taken to matrix A, wherein BA=EM, EMFor M rank unit matrix.Therefore it can be with reverse
Heat flux distribution vector α, i.e. α=B β, the combustion intensity curve being fitted by discrete point, reckoning obtain each ignition burner 9
Current gas transmission oil condition, i.e., current heat flux distribution.
The heat flux distribution that above-mentioned mimetic design method is back-calculated to obtain obtains Fig. 4 temperature distortion map after simulation test, by with
Known temperature distortion map compares, especially the area and orientation in high temperature distortion area 11, and then simulates true hot-fluid point
Cloth.The waste of manpower and material resources caused by the invention avoids tests due to a large amount of randomness is attempted, substantially reduces test week
Phase；Mimetic design method only needs to set up the database of the matrix A with mapping principle simultaneously, can be from different temperature distortion
Map, which sets out, is quickly obtained corresponding heat flux distribution, reduces testing expense significantly compared to conventional method.
Claims (1)
1. a kind of temperature distortion map mimetic design method based on discrete series, it is characterised in that the following steps are included:
1) according to given measurement section temperature map distribution, speed of incoming flow and upstream distortion section and downstream map section are determined
The distance between；
2) nozzle quantity M and nozzle are generated according to temperature to be distributed, serial number is carried out to the arranged distribution of nozzle, and by each nozzle
Hot-fluid composite sequence be set as vector α；
3) the target map section in downstream is divided into the unit of magnitude N, by the minute cells got with horizontal direction
For zero degree line, one encloses and carries out minute cells sequence outward, and is given using interpolation by the way of based on temperature distortion map N number of
Unit carries out temperature assignment, and is denoted as map column vector β；
4) column vector Q is constructed respectively1,…,Qi,…,QM, wherein QiIt is denoted as (q1,…,qi,…,qM)T, remove q1It is set as except 1,
Other numerical value are set as 0, that is, indicate to be in maximum State of Thermal Liquid Based except i-th of nozzle, and other M-1 are in closed state,
In, maximum State of Thermal Liquid Based is denoted as 1, and minimum thermal flux state is denoted as 0；
5) carry out i-th of nozzle respectively to grind in maximum hot-fluid, the other M-1 numerical simulations being in close state or test
Study carefully, measure the temperature distortion map in downstream, and with reference to the number of step 3), obtains vector (a1i, a2i, a3i…aNi)T, M in total
Nozzle forms matrix
6) according to A α=β, generalized inverse matrix B is taken to matrix A, wherein BA=EM, EMFor M rank unit matrix, reverse heat flux distribution
Vector α, i.e. α=B β, so that it is determined that the distribution of hot-fluid, wherein maximum value 1, minimum value 0 in vector α；
7) according to resulting vector α, the state of each nozzle in upstream is obtained, i.e., realizes specific temperature by adjusting hot-fluid injection intensity
Distortion pattern is spent, obtained result provides data supporting for the temperature distortion probed under real working condition, therefore this mimetic design method is
To use matrix A and column vector β reverse column vector α.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112033683A (en) * | 2020-09-09 | 2020-12-04 | 中国航发沈阳发动机研究所 | Distortion device |
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| CN102980874A (en) * | 2011-09-07 | 2013-03-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for making map for detecting microporosity |
| CN104298826A (en) * | 2014-10-10 | 2015-01-21 | 南京航空航天大学 | Aerodynamic stability predicting and estimating method of aerial engine under counter thrust state |
| US20180345649A1 (en) * | 2017-06-05 | 2018-12-06 | The Boeing Company | Multi-region temperature controlled base for additive manufacturing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102980874A (en) * | 2011-09-07 | 2013-03-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for making map for detecting microporosity |
| CN104298826A (en) * | 2014-10-10 | 2015-01-21 | 南京航空航天大学 | Aerodynamic stability predicting and estimating method of aerial engine under counter thrust state |
| US20180345649A1 (en) * | 2017-06-05 | 2018-12-06 | The Boeing Company | Multi-region temperature controlled base for additive manufacturing |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112033683A (en) * | 2020-09-09 | 2020-12-04 | 中国航发沈阳发动机研究所 | Distortion device |
| CN112033683B (en) * | 2020-09-09 | 2022-12-16 | 中国航发沈阳发动机研究所 | Distortion device |
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