|Table of Contents|

Thermodynamic performance analysis of anovel precooled airbreathing engine layout(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2021年06期
Page:
62-75
Research Field:
专刊
Publishing date:

Info

Title:
Thermodynamic performance analysis of anovel precooled airbreathing engine layout
Author(s):
ZOU Zhengping1; 2; WANG Yifan1; DU Pengcheng2; NAN Xiangyi3; MA Yuan3
(1. National Key Laboratory of Science and Technology onAero-Engine and Aero-Thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 102206,China 2. Research Institute of Aero-Engine,Beihang University,Beijing 102206,China 3. Xian Aerospace Propulsion Institute,Xian 710100,China)
Keywords:
hypersonic precooled airbreathing engine thermodynamic cycle closed-loop helium cycle overall performance control law
PACS:
V231.9
DOI:
-
Abstract:
In order to consider the specific impulse and system complexity at the same time,a new hypersonic precooled airbreathing engine thermodynamic cycle layout which coupled with closed-loop helium cycle was proposed. This thermodynamic cycle layout adopts moderate air precooling,and a relatively simple two branch splitting,cooling and recompression pattern is adopted in the closed-loop helium cycle. In the first branch,less liquid hydrogen is used to ensure that helium was chilled to lower temperature,making helium easy to be compressed,so as to increase the pressure ratio of closed-loop cycle and then increase the output power of the closed-loop cycle. In the second branch,the hydrogen with relatively lower temperature is further used to cool the high-temperature helium form the precooler to ensure that the helium temperature after mixing meets the requirements of the precooler. Firstly,the parametric analysis and optimization of the design point performance of precooled airbreathing engine were carried out,and the engine specific impulse at Mach 5 working point can reach 3 287 s. By adjusting the equivalence ratio of bypass ramjet combustor and nozzle throat area,matched working of the intake,precooled turbine channel and bypass ramjet channel can be achieved,and the amount of fuel for cooling and combustion can be balanced. The engine thrust can be effectively regulated by adjusting the base pressure of closed-loop helium cycle,and all the main components can work stably. The overall engine performance calculated along a typical flight trajectory shows that this new precooled airbreathing engine has high thrust and specific impulse in the working range of Mach 0～5. The closed-loop helium cycle layout is relatively simple and easier to achieve engineering realization. Thus this new thermodynamic cycle layout can offer a new idea for the design of hypersonic precooled airbreathing engine.

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