CN113722900B - Performance design and analysis method for non-design point of aviation heat exchanger - Google Patents
Performance design and analysis method for non-design point of aviation heat exchanger Download PDFInfo
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- CN113722900B CN113722900B CN202110957282.4A CN202110957282A CN113722900B CN 113722900 B CN113722900 B CN 113722900B CN 202110957282 A CN202110957282 A CN 202110957282A CN 113722900 B CN113722900 B CN 113722900B
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Abstract
The invention relates to the technical field of aeroengines, in particular to a method for designing and analyzing performance of non-design points of an aero heat exchanger. According to the invention, through complex working condition input of the aviation heat exchanger, analysis of flow resistance and heat exchange characteristics of two fluids, calculation of relative distribution of flow resistance and heat exchange performance of two fluids, definition of relative relation of heat exchange performance of two fluids, calculation of relative distribution of overall heat exchange performance, calculation of relative distribution of heat exchange requirements of all non-design points, and analysis of dangerous working condition areas of flow resistance and heat exchange, dangerous point screening and non-design point performance analysis of the aviation heat exchanger under complex input working condition conditions are realized, and a new thought is provided for multi-working condition design and performance evaluation of the aviation heat exchanger.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a method for designing and analyzing performance of non-design points of an aero heat exchanger.
Background
The technology in the aerospace field is increasingly innovated, and the development of the aerospace technology in the last two decades has advanced to a new step in high altitude, high speed and high efficiency. The working area of the aircraft is widened by high altitude and high speed, so that the change of the flight working condition is more severe; high speeds will place the aircraft in a more severe thermal environment and the necessary thermal protection or management means must be employed to effectively distribute the aircraft thermal load. Under such a background, heat exchangers are increasingly being widely used in the aerospace field as key components for accomplishing mass-energy transport within an aircraft energy system.
Aiming at the characteristics of wide working range, high temperature and high pressure and the like of the heat exchanger in the aerospace field, the design and performance calculation method of the heat exchanger are necessary to be improved correspondingly. The traditional heat exchanger design and analysis method is that on the premise of determining the heat exchanger design point, the structural design of the heat exchanger design point is completed, and then the flow heat exchange performance of the heat exchanger under other non-design working conditions is checked. In a general flow, the design points of the heat exchanger are often selected to be consistent with the main operating points of the engine (maximum heat load conditions, minimum aerodynamic conditions, or cruise conditions). The flow resistance and heat exchange dangerous working condition of the heat exchanger are related to the heat exchanger structure, the heat exchange performance of the inner side and the outer side and other factors, and often do not coincide with the main working point of the engine. Therefore, the heat exchanger designed by the traditional method cannot be applied to all working conditions, and the heat transfer performance or the flow resistance performance cannot meet all non-design points at the same time, which brings serious difficulties to performance evaluation of the design and the non-design points of the aviation heat exchanger applied to the full-flight working conditions.
Disclosure of Invention
Aiming at the problems existing in the background technology, the design and analysis method for the performance of the non-design point of the aviation heat exchanger is provided. According to the invention, through complex working condition input of the aviation heat exchanger, analysis of flow resistance and heat exchange characteristics of two fluids, calculation of relative distribution of flow resistance and heat exchange performance of two fluids, definition of relative relation of heat exchange performance of two fluids, calculation of relative distribution of overall heat exchange performance, calculation of relative distribution of heat exchange requirements of all non-design points, and analysis of dangerous working condition areas of flow resistance and heat exchange, dangerous point screening and non-design point performance analysis of the aviation heat exchanger under complex input working condition conditions are realized, and a new thought is provided for multi-working condition design and performance evaluation of the aviation heat exchanger.
The invention provides a method for designing and analyzing performance of non-design points of an aviation heat exchanger, which comprises the following steps:
s1, inputting complex working conditions of an aviation heat exchanger: acquiring a working condition parameter boundary of the aviation heat exchanger in a flight envelope for the input condition of the method;
s2, two-flow fluid flow resistance and heat exchange characteristic analysis: analyzing the fluid flow heat exchange characteristics of the two sides of the dividing wall type heat exchanger on the basis of a flow heat exchange characteristic database of various heat exchange structures;
s3, calculating the relative distribution of flow resistance and heat exchange performance of two streams of fluid: on the premise of not considering the structural parameters of the heat exchanger, processing the flow parameters and the physical parameters to obtain the relative values of flow resistance and heat exchange performance;
s4, defining the relative relation between the heat exchange performance of two streams of fluid: the ratio of the maximum convection heat exchange coefficient to the minimum convection heat exchange coefficient at the two sides is introduced to determine the relative relation between the heat exchange intensity at the two sides;
s5, calculating the relative distribution of the overall heat exchange performance: based on the relative distribution of the heat exchange performance and the relative strong and weak relation of the heat exchange performance of the two streams of fluid, calculating the relative distribution of the total heat transfer coefficient of the heat exchanger;
s6, calculating the heat exchange requirement relative distribution of all non-design points: calculating heat exchange quantity and average temperature difference required by all working conditions according to the input complex working conditions of the aviation heat exchanger;
s7, analyzing the flow resistance and heat exchange dangerous working condition areas: according to the obtained relative distribution of the flow resistance performance and the overall relative distribution of the heat exchange performance, the relative dangerous degree of the flow resistance and the heat exchange is calculated according to the flow resistance limit and the heat exchange limit respectively.
Preferably, analysis of flow resistance and heat exchange characteristics of two streams of fluid and calculation of relative distribution of flow resistance and heat exchange performance of two streams of fluid are based on flow heat exchange characteristics of a heat exchange unit, and the relation of power of dimensionless numbers is extracted, so that the structure is subjected to primary fuzzy treatment.
Preferably, the heat exchange performance relative relation of the two streams defines a dimensionless parameter which takes the ratio of characteristic points as the relative relation of the heat exchange performance of the two sides according to the calculation result of the flow resistance and the heat exchange performance relative distribution of the two streams.
Preferably, the characteristic points include, but are not limited to, maximum and minimum points of heat exchange performance.
Preferably, the calculation of the overall heat exchange performance relative distribution is performed according to the calculation mode of the overall heat transfer coefficient and the relative distribution of the heat exchange performance of the two fluids, and the calculation analysis is performed by combining the relative relationship of the heat exchange performance of the two sides.
Preferably, the analysis of the flow resistance and heat exchange dangerous working condition areas needs to define the flow resistance dangerous degree and the heat exchange dangerous degree, and the maximum value area and the minimum value area of the flow resistance dangerous degree and the heat exchange dangerous working condition area are taken as final flow resistance and heat exchange dangerous working condition areas by taking the two parameters as references.
Preferably, the relative distribution of the degree of risk of flow resistance and the degree of risk of heat exchange reflects the non-design point performance of the heat exchanger under complex operating conditions.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the invention, through complex working condition input of the aviation heat exchanger, analysis of flow resistance and heat exchange characteristics of two fluids, calculation of relative distribution of flow resistance and heat exchange performance of two fluids, definition of relative relation of heat exchange performance of two fluids, calculation of relative distribution of overall heat exchange performance, calculation of relative distribution of heat exchange requirements of all non-design points, and analysis of dangerous working condition areas of flow resistance and heat exchange, dangerous point screening and non-design point performance analysis of the aviation heat exchanger under complex input working condition conditions are realized, and a new thought is provided for multi-working condition design and performance evaluation of the aviation heat exchanger.
Drawings
FIG. 1 is a flow chart of steps of an embodiment of the present invention.
Detailed Description
As shown in fig. 1, the method for designing and analyzing the performance of the non-design point of the aviation heat exchanger provided by the invention comprises the following steps: the method comprises the steps of inputting complex working conditions of the aviation heat exchanger, analyzing flow resistance and heat exchange characteristics of two fluids, calculating the relative distribution of the flow resistance and the heat exchange performance of the two fluids, defining the relative relation of the heat exchange performance of the two fluids, calculating the relative distribution of the whole heat exchange performance, calculating the relative distribution of heat exchange requirements of all non-design points, and analyzing the flow resistance and the heat exchange dangerous working condition areas.
The step of acquiring the working condition input of the aviation heat exchanger comprises the steps of acquiring the change of the flow, the temperature and the pressure of fluid inlets at two sides of the position of the heat exchanger along with the flight state by upstream input or calculation by overall performance based on the external environment and the internal working condition of the aircraft; and meanwhile, according to the requirements of all working conditions, the flow resistance limit and the heat exchange quantity limit of all working conditions are given.
Subsequently, the heat exchange dimensionless number Nu, the flow resistance dimensionless number f, and the power of the flow dimensionless number Re are extracted based on a variety of heat exchange unit structures including, but not limited to, cross flow and forward flow sweep tube bundle, longitudinal sweep tube bundle, fin tube bundle, plate-fin, circular fin tube, microchannel. And neglecting structural parameters, and reserving working medium flow and physical parameters to obtain the relative heat exchange performance distribution and the relative flow resistance distribution of the two fluids. The range of exponentiations of dimensionless numbers is used to cover various forms of heat exchange structures, wherein the fluid Nu of the two sides is generally proportional to the power of 0.4-0.95 of the Reynolds number Re, the fluid flow resistance coefficient f of the two sides is generally proportional to the power of 0.3-0.4 of the Plandter number Pr, and the fluid flow resistance coefficient f of the two sides is generally proportional to the power of-0.4-0.2 of the Reynolds number Re.
And defining the ratio of the heat exchange coefficients of the highest point (or other characteristic values such as the minimum value or average value) of the heat exchange performance of the two streams as gamma based on the obtained relative heat exchange performance distribution of the two streams, so as to determine the specific gravity of the relative heat exchange performance of the two streams affecting the whole heat exchange performance. The side with relatively poor heat exchange performance has a greater influence on the overall heat exchange performance. And obtaining the relative distribution of the total heat transfer coefficient K according to the integral heat transfer coefficient calculation formula. And then, according to the input complex working conditions of the aviation heat exchanger, determining the distribution of the required heat exchange quantity Q of each working condition and the distribution of the average heat transfer temperature difference dT of each working condition.
And defining the overall heat exchange discrimination parameters as Q and (dT.K), and obtaining the relative distribution of the discrimination parameters in all working condition ranges according to the relative distribution of the total heat transfer coefficient K and the distribution of Q and dT. The higher the overall heat exchange discrimination parameter is, the easier the heat exchange is to realize; and the lowest point of the overall heat exchange judging parameter corresponds to a working condition, and heat exchange is relatively difficult to realize, namely a heat exchange dangerous point. In the design flow of the heat exchanger, the heat exchange quantity of heat exchange dangerous points is ensured, and the heat exchange quantity of all other working condition points can be ensured to meet the requirement. Similarly, for the upper limit and the lower limit of the temperature of certain working media, an upper limit is provided for heat exchange quantity, and the working condition corresponding to the highest point of the overall heat exchange discrimination parameters is taken as a temperature limiting dangerous point and is incorporated into the design flow of the heat exchanger.
For the flow resistance of the fluid at two sides, the obtained two-flow-path relative flow resistance distribution is adopted, and the working condition corresponding to the maximum value of the two-flow-path relative flow resistance is respectively taken as the flow resistance dangerous point. In the design flow of the heat exchanger, the flow resistance of the fluid at the two sides of the flow resistance dangerous point is ensured, and the flow resistance at the two sides of all other working condition points can be ensured to meet the requirements.
In addition, the relative distribution of the overall heat exchange discrimination parameters and the relative flow resistance distribution of two fluids are used for determining the heat exchange dangerous point, the temperature limiting dangerous point and the flow resistance dangerous point, the distribution itself reflects the performance of the heat exchanger at the non-design point under the complex working condition of the aviation heat exchanger, and the flow resistance and the heat exchange characteristic area can be determined from the distribution.
Further, the above sum refers to 4 variables, the power exponent a of Re and the power exponent b of Pr in the empirical relation of the two-side fluid Nu, the power exponent c of Re in the empirical relation of the two-side fluid flow resistance coefficient f, and the heat exchange coefficient ratio gamma of the highest point of the heat exchange performance of the two fluids defined above. Where a is typically in the range of [0.4,0.95], b is typically in the range of [0.3,0.4], c is typically in the range of [ -0.4, -0.2], the theoretical value range of gamma is (0, +++). Traversing the value ranges of a, b and gamma to obtain all possible heat exchange dangerous operating points and temperature limiting dangerous operating points of the heat exchanger with any structure; and traversing the value range of c to obtain dangerous operating points of fluid flow resistance on all possible two sides of the heat exchanger with any structure. The set of all dangerous working condition points is the final dangerous working condition area, and for the heat exchanger with any structure, the dangerous working condition area is considered for design during design, so that the flow resistance and heat exchange requirements of the whole working condition area can be met.
Furthermore, the flow resistance and the heat exchange performance obtained in the parameter traversing process are distributed relatively, so that the performance of the relatively non-design point of the given working condition under the condition of any heat exchanger structure can be reflected.
The implementation flow realizes the performance analysis of dangerous point screening and non-design points under the complex input working condition of the aviation heat exchanger, and provides a new thought for multi-working-condition design and performance evaluation of the aviation heat exchanger.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited thereto, and various changes can be made within the knowledge of those skilled in the art without departing from the spirit of the present invention.
Claims (6)
1. The method for designing and analyzing the performance of the non-design point of the aviation heat exchanger is characterized by comprising the following steps:
s1, inputting complex working conditions of an aviation heat exchanger: acquiring a working condition parameter boundary of the aviation heat exchanger in a flight envelope for the input condition of the method;
s2, two-flow fluid flow resistance and heat exchange characteristic analysis: based on the flow heat exchange characteristics of the heat exchange unit, extracting the power relation between the heat exchange dimensionless number Nu, the flow resistance dimensionless number f and the flow dimensionless number Re, and performing primary fuzzy processing on the structure; analyzing the fluid flow heat exchange characteristics of the two sides of the dividing wall type heat exchanger on the basis of a flow heat exchange characteristic database of various heat exchange structures;
s3, calculating the relative distribution of flow resistance and heat exchange performance of two streams of fluid: on the premise of not considering the structural parameters of the heat exchanger, processing the flow parameters and the physical parameters to obtain the relative values of flow resistance and heat exchange performance;
s4, defining the relative relation between the heat exchange performance of two streams of fluid: the ratio of the maximum convection heat exchange coefficient to the minimum convection heat exchange coefficient at the two sides is introduced to determine the relative relation between the heat exchange intensity at the two sides;
s5, calculating the relative distribution of the overall heat exchange performance: based on the relative distribution of the heat exchange performance and the relative strong and weak relation of the heat exchange performance of the two streams of fluid, calculating the relative distribution of the total heat transfer coefficient of the heat exchanger;
s6, calculating the heat exchange requirement relative distribution of all non-design points: calculating the required heat exchange amount and the average temperature difference of all working conditions according to the input complex working conditions of the aviation heat exchanger, and determining the distribution of the required heat exchange amount Q of each working condition and the distribution of the average heat transfer temperature difference dT of each working condition;
s7, analyzing the flow resistance and heat exchange dangerous working condition areas: calculating the relative dangerous degree of flow resistance and heat exchange according to the flow resistance limit and the heat exchange limit respectively according to the obtained relative distribution of flow resistance performance and the obtained relative distribution of overall heat exchange performance; defining the overall heat exchange discrimination parameters as Q and (dT.K), and acquiring the relative distribution of the discrimination parameters in all working condition ranges according to the relative distribution of the total heat transfer coefficient K and the distribution of Q and dT; the higher the overall heat exchange discrimination parameter is, the easier the heat exchange is to realize; and the lowest point of the overall heat exchange judging parameter corresponds to a working condition, and heat exchange is relatively difficult to realize, namely a heat exchange dangerous point.
2. The method for designing and analyzing the performance of non-design points of an aviation heat exchanger according to claim 1, wherein the relative relation between the heat exchange performance of two streams is defined according to the calculation result of the relative distribution of the flow resistance and the heat exchange performance of two streams, and the ratio of characteristic points is used as a dimensionless parameter of the relative relation between the heat exchange performance of two sides.
3. A method of designing and analyzing non-design point performance of an aircraft heat exchanger according to claim 2, wherein the characteristic points include, but are not limited to, maximum and minimum points of heat exchange performance.
4. The method for designing and analyzing the performance of the non-design point of the aviation heat exchanger according to claim 1, wherein the calculation of the overall heat exchange performance relative distribution is performed according to the calculation mode of the overall heat transfer coefficient and the relative distribution of the heat exchange performance of the two fluids, and the calculation and the analysis are performed by combining the relative relationship of the heat exchange performance of the two sides.
5. The method for designing and analyzing the performance of the non-design point of the aviation heat exchanger according to claim 1, wherein the analysis of the areas of the dangerous condition of the flow resistance and the heat exchange requires defining the dangerous degree of the flow resistance and the dangerous degree of the heat exchange, and taking the areas of the maximum value and the minimum value of the dangerous degree of the flow resistance and the dangerous degree of the heat exchange as the final areas of the dangerous condition of the flow resistance and the dangerous condition of the heat exchange by taking the two parameters as references.
6. The method for designing and analyzing the performance of the non-design point of the aviation heat exchanger according to claim 5, wherein the relative distribution of the risk degree of flow resistance and the risk degree of heat exchange reflects the performance of the non-design point of the heat exchanger under the complex working condition.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010006033A1 (en) * | 2008-07-08 | 2010-01-14 | Tao Of Systems Integration, Inc. | Method for predicting flow and performance characteristics of a body using critical point location |
| CN101705870A (en) * | 2009-12-03 | 2010-05-12 | 北京航空航天大学 | Air-oil heat exchanger suitable for gas turbine engine |
| WO2016003555A2 (en) * | 2014-07-01 | 2016-01-07 | Scanifly, LLC | Device, method, apparatus, and computer-readable medium for solar site assessment |
| CN113239474A (en) * | 2021-03-11 | 2021-08-10 | 中国科学院上海技术物理研究所 | Design method of pipe-sleeve heat exchanger for composite refrigerator in extremely-low temperature region |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109766589B (en) * | 2018-12-19 | 2020-08-14 | 西安交通大学 | Performance evaluation method for tube-fin heat exchanger under non-uniform head-on wind speed |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010006033A1 (en) * | 2008-07-08 | 2010-01-14 | Tao Of Systems Integration, Inc. | Method for predicting flow and performance characteristics of a body using critical point location |
| CN101705870A (en) * | 2009-12-03 | 2010-05-12 | 北京航空航天大学 | Air-oil heat exchanger suitable for gas turbine engine |
| WO2016003555A2 (en) * | 2014-07-01 | 2016-01-07 | Scanifly, LLC | Device, method, apparatus, and computer-readable medium for solar site assessment |
| CN113239474A (en) * | 2021-03-11 | 2021-08-10 | 中国科学院上海技术物理研究所 | Design method of pipe-sleeve heat exchanger for composite refrigerator in extremely-low temperature region |
Non-Patent Citations (1)
| Title |
|---|
| 航空发动机1次表面换热器流动换热性能分析;刘荫泽;张声宝;董威;刘振宇;于霄;;航空发动机(04);全文 * |
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