CN110083902B - Temperature distortion map inverse design method based on discrete sequence - Google Patents

Temperature distortion map inverse design method based on discrete sequence Download PDF

Info

Publication number
CN110083902B
CN110083902B CN201910307474.3A CN201910307474A CN110083902B CN 110083902 B CN110083902 B CN 110083902B CN 201910307474 A CN201910307474 A CN 201910307474A CN 110083902 B CN110083902 B CN 110083902B
Authority
CN
China
Prior art keywords
heat flow
map
vector
nozzles
temperature distortion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201910307474.3A
Other languages
Chinese (zh)
Other versions
CN110083902A (en
Inventor
尤延铖
李韧卓
朱剑锋
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xiamen University
Original Assignee
Xiamen University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Xiamen University filed Critical Xiamen University
Priority to CN201910307474.3A priority Critical patent/CN110083902B/en
Publication of CN110083902A publication Critical patent/CN110083902A/en
Application granted granted Critical
Publication of CN110083902B publication Critical patent/CN110083902B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • General Engineering & Computer Science (AREA)
  • Evolutionary Computation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)

Abstract

Temperature distortion map inverse design based on discrete sequenceThe method comprises the steps of determining the incoming flow velocity and the distance between an upstream distortion section and a downstream map section, numbering the arrangement distribution of nozzles, setting the heat flow combination sequence of each nozzle as a vector α, dividing a downstream target map section into units with the magnitude N, sorting the divided micro units outwards by taking the horizontal direction as a zero-angle line, and marking as a map column vector β, and respectively constructing a column vector Q1，...，Qi，...，QMThe method comprises the steps of measuring a downstream temperature distortion map, taking a generalized inverse matrix B from the matrix A to determine the distribution of heat flow, obtaining the states of all nozzles at the upstream according to a vector α, namely realizing the specific temperature distortion map by adjusting the injection intensity of the heat flow, and providing data support for temperature distortion under the actual working condition by the obtained result, so that the column vector α is reversely solved by using the matrix A and the column vector β.

Description

Temperature distortion map inverse design method based on discrete sequence
Technical Field
The invention relates to a pneumatic stability evaluation technology of an aircraft engine, in particular to a temperature distortion map inverse design method based on a discrete sequence for calculating the distribution condition of a heat source according to a temperature distortion map.
Background
The aerodynamic stability of an aircraft engine is an important index for evaluating the performance of the engine, and the engine is required to have excellent performance of a key design state, and can resist the interference of stability reduction factors in the whole flight envelope, so that a sufficient available stability margin is ensured (1 Zhao Yuanshi, an analysis system for the aerodynamic stability of the aircraft engine researches [ D ]. Nanjing aerospace university, 2013). However, in the processes of aircraft formation flying, missile launching and the like, the inlet of the engine inevitably sucks heat flow, the suction of the heat flow brings obvious temperature distortion to the inlet of the engine, the engine enters an unstable working state due to serious temperature distortion, and the deep knowledge of the temperature distortion problem has important significance for the design and development of future aero-engines.
In view of the important influence of temperature distortion on the stable operation of the engine, major aviation major countries such as the United states, the British, China, Russia and the like carry out mechanistic and systematic researches on the temperature distortion, and a corresponding temperature distortion generation and simulator design method is formulated (ice generation, leaf Wei. American and Russia aeroengines stability standard comparative analysis [ J ] aeronautical standardization and quality, 2009(02): 44-48). The existing temperature distortion is mainly characterized in that a certain number of nozzles are arranged in an air inlet channel, ignition combustion or heat flow injection is carried out at the nozzles, so that the local increase of the air flow temperature is realized, and the purpose of customizing a distortion measurement cross section map is realized by controlling the heat flow intensity of the nozzles. At present, in order to obtain a specified temperature distortion map, the main engineering practice is to study the heat flow intensity combination mode of the nozzles through a numerical simulation or test mode on the basis of determining the number of the nozzles and the distribution of the nozzles. Because the current customized design method of the temperature distortion map is lacked, a large amount of manpower and material resources are consumed in the fine debugging of the temperature distortion map, and the problems of long development period, complex design, high test randomness and the like exist, so that the search for the temperature distortion design method which can simply and conveniently obtain the complex temperature distortion map and can ensure the map accuracy is necessary.
Disclosure of Invention
The invention aims to provide a temperature distortion map inverse design method based on a discrete sequence, aiming at the defects of the existing temperature distortion map accurate design method and the like and calculating the distribution condition of a heat source according to the temperature distortion map.
The invention comprises the following steps:
1) determining the incoming flow velocity and the distance between the upstream distortion section and the downstream map section according to the given temperature map distribution of the measurement section;
2) generating the number M of nozzles and the nozzle distribution according to the temperature, sequentially numbering the arrangement distribution of the nozzles, and setting a heat flow combination sequence of each nozzle as a vector α;
3) respectively dividing the downstream target map cross section into units of magnitude N, sequencing the divided micro units in a circle outward by taking the horizontal direction as a zero-angle line, performing temperature assignment on the N units in an interpolation mode based on a temperature distortion map, and recording as a map column vector β;
4) respectively constructing a column vector Q1,…,Qi,…,QMWherein Q isiIs described as (q)1,…,qi,…,qM)TRemoving q1Except for setting to 1, other values are set to 0, namely, the other M-1 nozzles are in the off state except that the ith nozzle is in the maximum heat flow state, wherein the maximum heat flow state is marked as 1, and the minimum heat flow state is marked as 0;
5) respectively carrying out numerical simulation or experimental study of the ith nozzle in the maximum heat flow state and other M-1 nozzles in the closed state, measuring a downstream temperature distortion map, and referring to the serial number of the step 3) to obtain a vector (a)1i，a2i，a3i…aNi)TA total of M nozzles forming a matrix
Figure GDA0002511862620000021
6) According to A α - β, a generalized inverse matrix B is taken for the matrix A, wherein BA-EM，EMDetermining the distribution of the heat flow by reversely calculating a heat flow distribution vector α, namely α -B β for the M-order unit matrix, wherein the maximum value 1 and the minimum value 0 in the vector α;
7) according to the obtained vector α, the states of the nozzles at the upstream are obtained, namely, a specific temperature distortion map is realized by adjusting the injection intensity of the heat flow, and the obtained result provides data support for researching the temperature distortion under the real working condition, so that the reverse design method is to reversely solve the column vector α by using the matrix A and the column vector β.
The invention can analyze through the construction and solution of vector and matrix, wherein the heat flow discrete sequence distribution at the upstream is vector α, the flow temperature distribution at the downstream is vector β, the relation between the two is matrix A, and the construction methods of vector α, β and matrix A are detailed in the detailed description of the embodiment section.
The invention can reproduce the inverse design theory method of the real flow field shown by the temperature distortion map more accurately, namely, the existing temperature distortion map is taken as the target, the heat flow intensity distribution capable of forming the temperature distortion field shown by the map is obtained by inverse calculation under the arrangement state of a specific temperature nozzle, the distance between an upstream distortion simulator and a temperature distortion measuring section is generally a fixed value in consideration of the fact that the temperature distortion map is generally given under the specific incoming flow speed state, the quantity and the distribution of the nozzles for generating the temperature in the engineering are generally given, and the solution of the upstream temperature distortion simulator aiming at the temperature distortion map can be understood as follows: given a downstream flow temperature distribution, a relationship between the upstream heat flow and the downstream temperature distribution is constructed, and the discrete sequence of the upstream heat flow is solved reversely.
The invention considers that the quantity and the distribution of the nozzles generated by the temperature of the upstream section in engineering are generally given, the downstream temperature distortion space distribution is mainly processed by adjusting the heat flow intensity of the nozzles, the nozzle states with different heat flow intensities are processed in discrete sequences, and the interrelation among different nozzles can be understood as vector operation among different discrete sequences. And (3) combining the influence rule of the upstream heat flow on the downstream measurement section temperature distribution, constructing different nozzle state discrete sequences, and realizing the analysis of the forward influence rule of the upstream temperature distortion simulator on the downstream temperature distortion map. The so-called inverse design is that a discrete sequence combination of the upstream nozzles is searched by a known temperature distortion map, so that the design of the temperature distortion simulator is realized.
The invention has the following outstanding technical effects:
the invention can simulate the heat flow distribution under the real working condition and obtain the temperature distortion map with higher precision. Because the influence of each nozzle in the combustion section on the temperature measuring surface is quantized, the waste of manpower and material resources caused by a large number of random attempts in the test is avoided, and the test period is greatly shortened. Meanwhile, the inverse design method can quickly obtain corresponding heat flow distribution from different temperature distortion maps only by establishing a database of the matrix A with the mapping rule, and compared with the traditional method, the method obviously reduces the test cost.
Drawings
FIG. 1 is a schematic plan view of a temperature distortion testing apparatus.
Fig. 2 is a schematic diagram of a distribution of ignition nozzles in the combustion section of the test section of fig. 1 (M21).
Fig. 3 is a schematic diagram of a profile of the thermometric surface downstream of the test section of fig. 1 (N-40).
FIG. 4 is a schematic diagram of a temperature distortion map obtained by experimental simulation of a temperature sensing surface downstream of the test section of FIG. 1.
The labels in the figure are: 1 denotes a combustion section in the test section, 2 denotes a fuel pipe in the combustion section 1 in the test section, 3 denotes a mixing section in the test section, 4 denotes a temperature measuring surface downstream of the test section, 5 denotes a gas pipe in the combustion section 1 in the test section, 6 denotes a fixing rod in the combustion section 1 in the test section, 7 denotes an air inlet upstream of the test section, 8 denotes a distance from a cross section of an ignition nozzle in the test section to the temperature measuring surface, 9 denotes an ignition nozzle, 10 denotes a temperature measuring point in the temperature measuring surface, and 11 denotes a high temperature distortion region in a temperature distortion map.
Detailed Description
The following examples will further illustrate the present invention with reference to the accompanying drawings.
The embodiment of the invention comprises the following steps:
1) determining the incoming flow velocity and the distance between the upstream distortion section and the downstream map section according to the given temperature map distribution of the measurement section;
2) generating the number M of nozzles and the nozzle distribution according to the temperature, sequentially numbering the arrangement distribution of the nozzles, and setting a heat flow combination sequence of each nozzle as a vector α;
3) respectively dividing the downstream target map cross section into units of magnitude N, sequencing the divided micro units in a circle outward by taking the horizontal direction as a zero-angle line, performing temperature assignment on the N units in an interpolation mode based on a temperature distortion map, and recording as a map column vector β;
4) respectively constructing a column vector Q1,…,Qi,…,QMWherein Q isiIs described as (q)1,…,qi,…,qM)TRemoving q1Except for setting to 1, other values are set to 0, namely, the other M-1 nozzles are in the off state except that the ith nozzle is in the maximum heat flow state, wherein the maximum heat flow state is marked as 1, and the minimum heat flow state is marked as 0;
5) respectively carrying out numerical simulation or experimental research on the ith nozzle in the maximum heat flow state and other M-1 nozzles in the closed state, and measuringA downstream temperature distortion map is obtained, and the vector (a) is obtained by referring to the number of the step 3)1i，a2i，a3i…aNi)TA total of M nozzles forming a matrix
Figure GDA0002511862620000041
6) According to A α - β, a generalized inverse matrix B is taken for the matrix A, wherein BA-EM，EMDetermining the distribution of the heat flow by reversely calculating a heat flow distribution vector α, namely α -B β for the M-order unit matrix, wherein the maximum value 1 and the minimum value 0 in the vector α;
7) according to the obtained vector α, the states of the nozzles at the upstream are obtained, namely, a specific temperature distortion map is realized by adjusting the injection intensity of the heat flow, and the obtained result provides data support for researching the temperature distortion under the real working condition, so that the reverse design method is to reversely solve the column vector α by using the matrix A and the column vector β.
The schematic plan view of the temperature distortion test device is shown in figure 1, the temperature distortion test device is basically the same as a traditional test device, ignition nozzles 9 (see figure 2) are mutually stable depending on fixed rods 6 in a combustion section 1 in a test section, fuel pipes 2 in the combustion section 1 in the test section and gas pipes 5 in the combustion section 1 in the test section are communicated with each nozzle, the length of a mixing section 3 in the test section is the distance 8 from the cross section of the ignition nozzles 9 to a temperature measuring surface 4 downstream of the test section, the heat flow distribution reversely deduced by the reverse design method is mainly shown on the cross section of the ignition nozzles in figure 2, the ignition nozzles 9 in the combustion section 1 in the test section are adjusted according to a result vector α of the reverse design method, data are obtained on the temperature measuring surface 4 downstream of the test section by using temperature measuring points 10 (see figure 3) in the temperature measuring surface, the temperature distortion simulation map in figure 4 is obtained after the data are processed, the data are compared with the known temperature distortion, and if the closeness degree is good, the simulated heat flow field can represent a real heat flow field.
The temperature distortion test section of the invention has two main sections, namely an upstream ignition nozzle cross section and a downstream temperature measuring surface. In actual operation, according to a given temperature distortion map, a temperature value of each unit is determined on a temperature measuring surface, and then heat flow distribution in a real working condition is simulated according to a reverse design method, wherein the method specifically comprises the following steps:
define the combustion intensity of the ith ignition nozzle as αiObtaining the heat flow distribution as vector α, and recording the temperature value obtained at each measuring point on the downstream temperature measuring surface as bjAll temperature values constitute an map column vector β.
Assume that at some point the heat flow distribution is α ═ (α)1,α2,...,αi,…,αM)TAnd the temperature at that time at a certain point j on the temperature measurement surface is affected by each nozzle based on factors other than the heat flow α respectivelyj1,αj2,...,αji,…,αjMThe values are measured from experiments, wherein the values of the rest nozzles can be calculated by only knowing the influence of three ignition nozzles on a certain axis on a downstream temperature measuring surface, and the influence of the point j under other factors is α according to the linear superposition principle of data pointsj1+αj2+αji+…+αjMThe above expression is multiplied by the combustion intensity α at the time of each nozzle before each termiThe total influence effect b of the temperature at the time point n can be obtainedjI.e. bj＝α1*αj1+α2*αj2+αi*αji+…+αM*αjM. Therefore, by analogy with the idea, a matrix A can be constructed to reflect the mapping rule of the temperature influence of the upstream heat source on the downstream temperature measurement surface:
Figure GDA0002511862620000051
according to A α - β, a generalized inverse matrix B is taken for the matrix A, wherein BA-EM，EMFor an M-order identity matrix, the heat flow distribution vector α, i.e., α — B β, can be inverted to determine the heat flow distribution.
The invention avoids the waste of manpower and material resources caused by a large amount of random attempts in the test, and greatly shortens the test period; meanwhile, the inverse design method can quickly obtain corresponding heat flow distribution from different temperature distortion maps only by establishing a database of the matrix A with the mapping rule, and compared with the traditional method, the method obviously reduces the test cost.
As shown in figures 1-4, the device comprises a combustion section 1 in a test section, a fuel pipe 2 in the combustion section 1 in the test section, a mixing section 3 in the test section, a temperature measuring surface 4 at the downstream of the test section, a gas conveying pipe 5 in the combustion section 1 in the test section, a fixing rod 6 in the combustion section 1 in the test section, a gas inlet 7 at the upstream of the test section, a distance 8 from the cross section of an ignition nozzle in the test section to the temperature measuring surface, an ignition nozzle 9, a temperature measuring point 10 in the temperature measuring surface and a high-temperature distortion area 11 in a temperature distortion map.
Firstly, the distance 8 from the cross section of the ignition nozzle to the temperature measuring surface is determined according to the type of the engine. Then, the 12 ignition nozzles 9 are sequentially numbered in accordance with the arrangement distribution thereof in accordance with the operating state of the engine, and a combustion intensity function curve of each ignition nozzle 9 is calculated.
The numbering rules are as follows:
on the circular section of the heat source, a ray is horizontally led out to the right by taking the center of a circle as a vertex, is set as a horizontal reference line, namely a 0-degree line, and is rotated to be positive anticlockwise. The horizontal reference line is rotated in the forward direction and the ignition nozzles are hit by pieces, wherein the ignition nozzles 9 on the same ray are numbered in order from the center of the circle outward in the radial direction. The M ignition nozzles 9 are ordered in sequence according to the numbering described above.
The combustion intensity of each ignition nozzle is obtained by adjusting gas transmission and oil supply, the maximum combustion intensity is theoretically determined to be 1, the minimum value is 0, and the rest values are obtained between 0 and 1.
And dividing the downstream target map cross section into units of magnitude N, sequencing the divided micro units by taking the horizontal direction as a zero-angle line and taking the micro units one circle outwards, assigning temperatures to the N units in an interpolation mode based on the temperature distortion map, and recording as a map column vector β.
Controlling the ith ignition nozzle to operate, and remaining M-1 ignition nozzles to be closed, namely Qi＝(q1,…,qi,…,qM)TWherein q isiSetting the maximum heat flow state as 1, setting other values as 0, recording the maximum heat flow state as 1 and recording the minimum heat flow state as 0, respectively carrying out numerical simulation or experimental study on the ith ignition nozzle in the maximum heat flow state and other M-1 ignition nozzles in the closed state, measuring a downstream temperature distortion map, and referring to the numbering rule of the downstream target map section to obtain a vector (α)1i,α2i,...,α3i,…,αNi)T. A total of M ignition nozzles 9 may form a matrix
Figure GDA0002511862620000061
According to A α - β, a generalized inverse matrix B is taken for the matrix A, wherein BA-EM，EMThe heat flow distribution vector α, namely α -B β, can be obtained by inverse calculation of the heat flow distribution vector, namely, the combustion intensity curve obtained by fitting discrete points, and the current gas/oil supply state, namely, the current heat flow distribution of each ignition nozzle 9 can be obtained by calculation.
The heat flow distribution obtained by the inverse design method is inversely deduced, the temperature distortion map shown in the figure 4 is obtained after a simulation test, and the real heat flow distribution is simulated by comparing the temperature distortion map with the known temperature distortion map, particularly the area and the direction of the high-temperature distortion area 11. The invention avoids the waste of manpower and material resources caused by a large amount of random attempts in the test, and greatly shortens the test period; meanwhile, the inverse design method can quickly obtain corresponding heat flow distribution from different temperature distortion maps only by establishing a database of the matrix A with the mapping rule, and compared with the traditional method, the method obviously reduces the test cost.

Claims (1)

1. A temperature distortion map inverse design method based on discrete sequences is characterized by comprising the following steps:
1) determining the incoming flow velocity and the distance between the upstream distortion section and the downstream map section according to the given temperature map distribution of the measurement section;
2) generating the number M of nozzles and the nozzle distribution according to the temperature, sequentially numbering the arrangement distribution of the nozzles, and setting a heat flow combination sequence of each nozzle as a vector α;
3) respectively dividing the downstream target map cross section into units of magnitude N, sequencing the divided micro units in a circle outward by taking the horizontal direction as a zero-angle line, performing temperature assignment on the N units in an interpolation mode based on a temperature distortion map, and recording as a map column vector β;
4) respectively constructing a column vector Q1,…,Qi,…,QMWherein Q isiIs described as (q)1,…,qi,…,qM)TRemoving q1Except for setting to 1, other values are set to 0, namely, the other M-1 nozzles are in the off state except that the ith nozzle is in the maximum heat flow state, wherein the maximum heat flow state is marked as 1, and the minimum heat flow state is marked as 0;
5) respectively carrying out numerical simulation or experimental study of the ith nozzle in the maximum heat flow state and other M-1 nozzles in the closed state, measuring a downstream temperature distortion map, and referring to the serial number of the step 3) to obtain a vector (a)1i，a2i，a3i…aNi)TA total of M nozzles forming a matrix
Figure FDA0002030343550000011
6) According to A α - β, a generalized inverse matrix B is taken for the matrix A, wherein BA-EM，EMDetermining the distribution of the heat flow by reversely calculating a heat flow distribution vector α, namely α -B β for the M-order unit matrix, wherein the maximum value 1 and the minimum value 0 in the vector α;
7) according to the obtained vector α, the states of the nozzles at the upstream are obtained, namely, a specific temperature distortion map is realized by adjusting the injection intensity of the heat flow, and the obtained result provides data support for researching the temperature distortion under the real working condition, so that the reverse design method is to reversely solve the column vector α by using the matrix A and the column vector β.
CN201910307474.3A 2019-04-17 2019-04-17 Temperature distortion map inverse design method based on discrete sequence Active CN110083902B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910307474.3A CN110083902B (en) 2019-04-17 2019-04-17 Temperature distortion map inverse design method based on discrete sequence

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910307474.3A CN110083902B (en) 2019-04-17 2019-04-17 Temperature distortion map inverse design method based on discrete sequence

Publications (2)

Publication Number Publication Date
CN110083902A CN110083902A (en) 2019-08-02
CN110083902B true CN110083902B (en) 2020-07-31

Family

ID=67415313

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910307474.3A Active CN110083902B (en) 2019-04-17 2019-04-17 Temperature distortion map inverse design method based on discrete sequence

Country Status (1)

Country Link
CN (1) CN110083902B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112033683B (en) * 2020-09-09 2022-12-16 中国航发沈阳发动机研究所 Distortion device

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102980874B (en) * 2011-09-07 2015-01-28 沈阳黎明航空发动机(集团)有限责任公司 Method for making map for detecting microporosity
CN104298826B (en) * 2014-10-10 2017-10-31 南京航空航天大学 The prediction of aero-engine aerodynamic stability and appraisal procedure under a kind of thrust reversing rating
US10974497B2 (en) * 2017-06-05 2021-04-13 The Boeing Company Multi-region temperature controlled base for additive manufacturing

Also Published As

Publication number Publication date
CN110083902A (en) 2019-08-02

Similar Documents

Publication Publication Date Title
CN112550758B (en) Method for obtaining actual performance of each part of engine under complete machine condition
Chupp et al. Evaluation of internal heat-transfer coefficients for impingement-cooled turbine airfoils.
CN109409016B (en) Visualization method for unsteady flow of aero-engine compressor
CN110083902B (en) Temperature distortion map inverse design method based on discrete sequence
Villafañe et al. Aerodynamic impact of finned heat exchangers on transonic flows
Wolters et al. Engine performance simulation of the integrated V2527-Engine Fan
CN105203327A (en) Gas channel measurement parameter selecting method applied to engine gas channel analysis
Adamczuk et al. Time resolved full-annulus computations of a turbine with inhomogeneous inlet conditions
CN110160792A (en) A kind of dynamical system dynamic simulation test method
Arts et al. Aero-thermal performance of a two dimensional highly loaded transonic turbine nozzle guide vane: A test case for inviscid and viscous flow computations
Chriss et al. The effects of blade-row spacing on the flow capacity of a transonic rotor
Villafañe et al. Development of a transonic wind tunnel to investigate engine bypass flow heat exchangers
Zheng et al. The impact of uncertain stagger angle variation on high-pressure compressor rotor performance
Liu et al. Throughflow method for a combustion chamber with effusion cooling modelling
CN114077775B (en) Dynamic pressure intelligent measurement method for aeroengine
Manfredi et al. Loss measurement strategy in ORC supersonic blade cascades
Kannan et al. Automated multi-code URANS simulation of compressor-combustor components
Sivapragasam et al. An air jet distortion generation system
Anni et al. Numerical Simulation Analysis of Flow Field in Intake System of a Core Engine Test
Tschirner et al. Aerodynamic optimisation of an aeroengine bypass duct OGV-pylon configuration
CN116593168B (en) Method and system for evaluating fuel consumption rate of ramjet rotary detonation engine
Smith One-dimensional mean line code technique to calculate stage-by-stage compressor characteristics
Hoznedl et al. EXPERIMENTAL AND NUMERICAL RESEARCH ON FLOW IN THE LAST STAGE OF 1090MW STEAM TURBINE
Dfor L iATION PAGE
Davis et al. A Proposal for Integration of Wind Tunnel and Engine Test Programs for the Evaluation of Airframe-Propulsion Compatibility Using Numerical Simulations

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant