An engine thermodynamic cycle parameter analysis method and device

A thermodynamic cycle and parameter analysis technology, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of low design rationality and large selection range, and achieve precise thermal cycle parameter selection range and improve rationality , the effect of reducing the number of iterations

Active Publication Date: 2019-06-28
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology

[0006] The purpose of the present invention is to overcome the shortcomings of the above-mentioned prior art that the selection range is too large and the design rationality is low, and provide an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device with a suitable selection range and high design rationality

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  • An engine thermodynamic cycle parameter analysis method and device
  • An engine thermodynamic cycle parameter analysis method and device
  • An engine thermodynamic cycle parameter analysis method and device

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[0052] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0053] At present, when selecting the thermodynamic cycle parameters of turboshaft engines, the pressure ratio and the outlet temperature range of the combustion chamber are generally proposed based on the current component technology, materials and process level. System bleed air volume, calculate the engine power and fuel consumption rate under the conditions of multiple sets of pressure ratio and combustion chamber outlet t...

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Abstract

The invention relates to the technical field of engines, and provides an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device. The engine thermodynamic cycle parameter analysis method comprises the following steps: establishing a parameter coupling relationship among all parts of an engine; calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation; determining a strength limiting parameter of each part; and obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range. According to the engine thermodynamic cycle parameter analysis method, parameters of allparts are mutually coupled, and the thermodynamic cycle parameter selection range obtained through drawing is more accurate; the structural strength limitation of components such as a compressor and aturbine is considered, the thermodynamic cycle parameter selection range is further narrowed, and the performance design reasonability of the turboshaft engine is improved; The number of iterations of the turboshaft engine performance design is effectively reduced, and the project development period is shortened.

Description

technical field [0001] The invention relates to the technical field of aeroengines, in particular to an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device. Background technique [0002] Turboshaft engine thermodynamic cycle parameters include intake total pressure loss, compressor pressure ratio, adiabatic efficiency, combustion chamber outlet temperature, total pressure loss, turbine efficiency and exhaust total pressure loss, etc. Thermodynamic cycle parameter selection is the first step in turboshaft engine performance design, which determines the final performance of turboshaft engine. [0003] In the prior art, the selection range of the engine thermodynamic cycle parameter analysis method is too large, and the rationality of the design is low. [0004] Therefore, it is necessary to design a new engine thermodynamic cycle parameter analysis method and engine thermodynamic cycle parameter analysis device. ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 张鑫张平平李维刘渊张海彪
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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