CN113204842B - Engine thermodynamic cycle design method - Google Patents
Engine thermodynamic cycle design method Download PDFInfo
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- CN113204842B CN113204842B CN202110469268.XA CN202110469268A CN113204842B CN 113204842 B CN113204842 B CN 113204842B CN 202110469268 A CN202110469268 A CN 202110469268A CN 113204842 B CN113204842 B CN 113204842B
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000001816 cooling Methods 0.000 claims abstract description 22
- 238000004364 calculation method Methods 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims abstract description 5
- 230000000694 effects Effects 0.000 claims description 8
- 238000012938 design process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
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- G16C60/00—Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
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- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
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- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract
The application belongs to the technical field of engine design, and relates to an engine thermodynamic cycle design method, which comprises the following steps: s1, determining the highest temperature state according to the wall surface temperature of a turbine guider, and judging whether the material use requirement is met; s2, calculating heat exchange quantity according to the cooling requirement, and calculating the state performance of the engine after the heat exchanger is increased based on the total pressure loss initial value of the given external heat exchanger; and S3, judging whether the engine state performance after the heat exchanger is added meets the parameter design requirement, if not, changing the total pressure loss of the external heat exchanger, performing iterative calculation until the engine state performance meets the parameter design requirement, and outputting the overall machine performance parameter after the heat exchanger is added and the external heat exchanger performance parameter. The application provides a thermodynamic cycle design method, which is used for realizing the design of engine cycle parameters for improving the temperature of turbine blades by adopting an external heat exchanger and can quickly obtain more accurate design results.
Description
Technical Field
The application belongs to the technical field of engine design, and particularly relates to an engine thermodynamic cycle design method.
Background
In the future, the temperature in front of the turbine of the advanced aeroengine is continuously increased, so that the heat load of high-temperature parts such as turbine blades is greatly increased, however, the temperature in front of the turbine is limited by the metal temperature resistance, and in order to meet the requirement of continuously improving the temperature and the pressure ratio in front of the turbine, a new method for improving the cooling quality of cooling air is extremely necessary while the new cooling structure is continuously researched.
For the engine scheme of trying to adopt the external heat exchanger, the heat exchange quantity generated by the heat exchanger and the influence on different section parameters of the engine after cooling the turbine cold air are generally considered in the overall performance simulation process of the traditional engine, the performance of the engine is obtained through a repeated trial calculation mode, and the following problems exist: firstly, the influence of cooling of cold air on cooling performance cannot be reflected; secondly, the calculation efficiency is low, meanwhile, the optimal design result is difficult to obtain, and thirdly, if the design cost is greatly increased through repeated test iteration.
Disclosure of Invention
The invention aims to solve the technical problem of how to consider the improvement of the cooling effect of the turbine guide vane by adding the external heat exchanger in the design process of the turbofan engine scheme, realize the design of the turbofan engine thermodynamic cycle with the external heat exchanger and obtain the required design target of the external heat exchanger.
The engine thermodynamic cycle design method mainly comprises the following steps:
s1, determining the highest temperature state according to the wall surface temperature of a turbine guider, and judging whether the material use requirement is met;
s2, calculating heat exchange quantity according to the cooling requirement, and calculating the state performance of the engine after the heat exchanger is increased based on the total pressure loss initial value of the given external heat exchanger;
And S3, judging whether the engine state performance after the heat exchanger is added meets the parameter design requirement, if not, changing the total pressure loss of the external heat exchanger, performing iterative calculation until the engine state performance meets the parameter design requirement, and outputting the overall machine performance parameter after the heat exchanger is added and the external heat exchanger performance parameter.
Preferably, step S1 further comprises:
and S11, calculating the cooling effect of the turbine guide according to the inlet temperature of the turbine blades and the cool air temperature, and further determining the wall surface temperature of the turbine guide.
Preferably, in step S11, the calculation of the turbine blade inlet temperature and the cool air temperature is performed using a plurality of design points or typical points of the turbine blade.
Preferably, in step S11, the design point or typical point includes a turbine blade maximum heat load point.
Preferably, in step S11, the design point or typical point includes a turbine blade maximum aerodynamic load point.
Preferably, in step S11, the design point or typical point includes a highest pre-turbine temperature point.
Preferably, before step S11, the method includes:
And S10, obtaining the design point parameters and the control rules of non-design points of the overall scheme of the engine.
Preferably, in step S2, before calculating the heat exchange amount according to the cooling requirement, the method includes:
And acquiring a cooling effect curve of the turbine guide and cooling requirements of the turbine guide.
Preferably, in step S3, determining whether the engine state performance after adding the heat exchanger meets the parameter design requirement includes determining whether the state performance of the engine under a plurality of typical working conditions after adding the heat exchanger meets the parameter design requirement.
The application provides a thermodynamic cycle design method, which is used for realizing the design of engine cycle parameters for improving the temperature of turbine blades by adopting an external heat exchanger and can quickly obtain more accurate design results.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the engine thermodynamic cycle design method of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, are intended to fall within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
For the determined overall scheme, the application hopes to realize the improvement of the cooling effect by adding the external heat exchanger, reduce the wall temperature of the turbine blade and improve the service life of the blade. In the overall performance professional thermodynamic cycle design process, the heat exchange performance and the flow loss performance of the external heat exchanger need to be determined, so that the wall surface temperature of the blade can meet the allowable range, and meanwhile, the overall performance can be less influenced.
The application relates to a design method of engine thermodynamic cycle, which adopts an external heat exchanger to improve the temperature of turbine blades, and comprises the following steps:
s1, determining the highest temperature state according to the wall surface temperature of a turbine guider, and judging whether the material use requirement is met;
s2, calculating heat exchange quantity according to the cooling requirement, and calculating the state performance of the engine after the heat exchanger is increased based on the total pressure loss initial value of the given external heat exchanger;
And S3, judging whether the engine state performance after the heat exchanger is added meets the parameter design requirement, if not, changing the total pressure loss of the external heat exchanger, performing iterative calculation until the engine state performance meets the parameter design requirement, and outputting the overall machine performance parameter after the heat exchanger is added and the external heat exchanger performance parameter.
The engine thermodynamic cycle design of the present application is described in detail below in conjunction with FIG. 1:
a) First, performing design point calculation and typical point calculation of an engine scheme, wherein the calculation needs to include: the maximum heat load point of the turbine blade, the maximum aerodynamic load point of the turbine blade, the maximum temperature point before the turbine and the like, because the temperature of the wall surface of the turbine can be relatively high in the states, the working environment of the turbine blade is worst.
B) And according to the inlet temperature of the typical point turbine blade and the cold air temperature, obtaining the cold effect of the typical point turbine guide by applying a cold effect formula, and calculating the wall temperature of the turbine guide.
C) And determining the highest temperature state according to the wall temperature calculation result, primarily estimating the cooling requirement of the cold air at the highest wall temperature, respectively calculating the wall temperature of each typical point according to the cooled cold air result, and judging whether the material use requirement is met.
D) And determining the heat exchange amount according to the cooling requirement, giving an initial value of total pressure loss of the heat exchanger, and calculating the typical state performance of the engine after the heat exchanger is increased.
E) And evaluating whether the performance parameters after the heat exchanger is added meet the requirements, if not, iterating until the scheme meets the design target, completing the design of the thermodynamic cycle of the engine, and determining the design target of the external heat exchanger.
The conventional overall performance thermodynamic cycle analysis does not have the capability of analyzing the working environment of the blade, and is generally judged by adopting section parameters, the method is not direct enough, and the design requirement of the overall performance specialty on the external heat exchanger cannot be given.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. A method of engine thermodynamic cycle design employing an external heat exchanger to improve turbine blade temperature, the method comprising:
s1, determining the highest temperature state according to the wall surface temperature of a turbine guider, and judging whether the material use requirement is met;
s2, calculating heat exchange quantity according to the cooling requirement, and calculating the state performance of the engine after the heat exchanger is increased based on the total pressure loss initial value of the given external heat exchanger;
S3, judging whether the engine state performance after the heat exchanger is added meets the parameter design requirement, if not, changing the total pressure loss of the culvert heat exchanger, performing iterative calculation until the engine state performance meets the parameter design requirement, and outputting the overall machine performance parameter after the heat exchanger is added and the culvert heat exchanger performance parameter;
Wherein, step S1 further comprises: s11, calculating the cooling effect of the turbine guide according to the inlet temperature of the turbine blade and the cool air temperature, and further determining the wall temperature of the turbine guide; in step S11, the turbine blade inlet temperature and the cool air temperature are calculated using a plurality of design points or typical points of the turbine blade, including the turbine blade maximum aerodynamic load point, the turbine blade maximum thermal load point, and the maximum turbine pre-turbine temperature point.
2. The engine thermodynamic cycle design method as claimed in claim 1, wherein prior to step S11, comprising:
And S10, obtaining the design point parameters and the control rules of non-design points of the overall scheme of the engine.
3. The engine thermodynamic cycle design method as claimed in claim 1, wherein before calculating the heat exchange amount according to the cooling demand in step S2, comprising:
And acquiring a cooling effect curve of the turbine guide and cooling requirements of the turbine guide.
4. The engine thermodynamic cycle design method of claim 1, wherein in step S3, determining whether the engine state performance after adding the heat exchanger meets the parameter design requirement includes determining whether the engine state performance under a plurality of typical operating conditions after adding the heat exchanger meets the parameter design requirement.
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| CN202110469268.XA CN113204842B (en) | 2021-04-28 | 2021-04-28 | Engine thermodynamic cycle design method |
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| CN113204842B true CN113204842B (en) | 2024-05-24 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2608688Y (en) * | 2002-12-30 | 2004-03-31 | 沈阳黎明航空发动机(集团)有限责任公司 | External box-type heat exchanger for gas turbine engine |
| CN102305152A (en) * | 2011-05-20 | 2012-01-04 | 中国科学院工程热物理研究所 | Hybrid exhaust aircraft engine |
| CN105117561A (en) * | 2015-09-16 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Aero-engine external duct system design method |
| CN107908816A (en) * | 2017-10-13 | 2018-04-13 | 北京航空航天大学 | Aero-engine cooling and the integrated design method of cooling air based on hollow fan blade |
| RU2726861C1 (en) * | 2018-03-06 | 2020-07-16 | Владимир Константинович Литвинов | Gas turbine engine operating method and gas turbine engine |
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| US8495883B2 (en) * | 2007-04-05 | 2013-07-30 | Siemens Energy, Inc. | Cooling of turbine components using combustor shell air |
| US7593808B2 (en) * | 2007-08-07 | 2009-09-22 | Banks Gale C | Apparatus and method for engine performance evaluation |
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- 2021-04-28 CN CN202110469268.XA patent/CN113204842B/en active Active
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| CN2608688Y (en) * | 2002-12-30 | 2004-03-31 | 沈阳黎明航空发动机(集团)有限责任公司 | External box-type heat exchanger for gas turbine engine |
| CN102305152A (en) * | 2011-05-20 | 2012-01-04 | 中国科学院工程热物理研究所 | Hybrid exhaust aircraft engine |
| CN105117561A (en) * | 2015-09-16 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Aero-engine external duct system design method |
| CN107908816A (en) * | 2017-10-13 | 2018-04-13 | 北京航空航天大学 | Aero-engine cooling and the integrated design method of cooling air based on hollow fan blade |
| RU2726861C1 (en) * | 2018-03-06 | 2020-07-16 | Владимир Константинович Литвинов | Gas turbine engine operating method and gas turbine engine |
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