|Table of Contents|

Analysis of optimum performance and maximum state control law of PATR engine(PDF)

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

Issue:
2023年06期
Page:
90-99
Research Field:
目次
Publishing date:

Info

Title:
Analysis of optimum performance and maximum state control law of PATR engine
Author(s):
MA Wenyou1;  MA Yuan1;  MA Haibo1;  YU Xuanfei2;  WU Yizhen1
1.Xi'an Aerospace Propulsion Institute, Xi'an 710100, China; 2.School of Aerospace, Northwestern Polytechnical University, Xi'an 710072, China
Keywords:
pre-cooling combined cycle engine;  PATR;  control law;  optimum performance state;  maximum thrust state;  maximum specific impulse state
PACS:
V236
DOI:
-
Abstract:
In order to study the control law of the maximum state(the maximum thrust state and the maximum specific impulse state)of the pre-cooling air turbine rocket engine(PATR), a steady state variable condition model of PATR was established, and the influence of the control parameter on the performance parameters of the engine was studied.The optimal performance state(maximum thrust state and specific impulse state at the same time)of the engine was given on the premise that the total hydrogen flow rate is proposed.On this basis, the control laws of the maximum thrust state and the maximum specific impulse state of the engine were proposed, and the flight envelope of the engine in the maximum thrust state and the maximum specific impulse state were given, respectively.The results show that the thrust of PATR engine will increase with the increase of main combustion chamber temperature, helium turbine inlet temperature and nozzle throat area when the total hydrogen flow rate is constant.When the temperature of the main combustion chamber, the inlet temperature of the helium turbine and the throat area of the nozzle are constant, the thrust increases with the increase of the total hydrogen flow.The optimal performance state control law of PATR engine with given total hydrogen flow rate is as follows: the sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the inlet temperature of the helium turbine and the throat area of the tail nozzle get the maximum value, and the thrust and specific impulse of the engine reach the maximum at the same time, and the engine is in the optimal performance state.The maximum thrust state control rules of the PATR engine are as follows.The sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the maximum value of the inlet temperature of the helium turbine and the throat area of the tail nozzle are obtained respectively.The total hydrogen flow rate should be increased as far as possible, when the total hydrogen flow rate is increased, the engine will touch the air compressor conversion speed or the maximum pressure boundary of the helium circuit.Safety boundary contact order is determined by engine characteristics and flow conditions.The maximum specific impulse state control law of PATR engine is as follows. The sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the maximum of the inlet temperature of the helium turbine and the throat area of the tail nozzle are obtained, and the total hydrogen flow rate should be reduced as far as possible, when the total hydrogen flow rate is reduced, the engine will touch the surge boundary of the air compressor or the maximum temperature boundary of the precooler material.Safety boundary contact sequence is also determined by engine characteristics and incoming flow conditions.

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