RDTT flow controller

Contents

INTRODUCTION

1. FLOW CONTROLLER DESIGN DESCRIPTION

2. INPUT DATA

3. CALCULATION OF FLOW REGULATOR CONTROL PARAMETERS

3.1 Calculation of parameters at different pressure

3.4 Determination of regulator inlet section area depending on central body travel

3.5 Calculation of pressure in control chamber

CONCLUSION

LIST OF SOURCES USED

Introduction

Connecting element between gas generator and RPD combustion chamber is fuel flow control unit with nozzle holes providing supercritical pressure drop between gas generator and combustion chamber at any modes of gas generator operation.

The calculation of nozzle holes of the gas generator is carried out during the design of the unit for regulating the flow rate of combustion products of the gas generator. In the absence of the control unit, the dimensions of the nozzle holes of the gas generator are calculated for the designed pressure in the gas generator in order to ensure the specified pressure in it during the entire operation time of the propulsion system.

The problem of creating a RPD with a controlled flow rate of propulsion fuel combustion products is mainly associated with the development of a reliable flow controller, optimizing its weight and size characteristics and developing a control system for the flow regulator as an executive link of the engine automatic control system (ECS).

Since the flow controller operates under conditions of high-speed and high-temperature two-phase flow of combustion products coming from the gas generator, experiments have shown that its reliable operation can be ensured using composite materials.

Flow Controller Design Description

The flow rate is controlled by changing the area of the nozzle holes. To do this, a two-stage flow controller is used. Two-stage flow regulator consists of nozzle insert, union for supply of working control gas, rear wall, channel for supply of working control gas, nozzle holes, rod, intermediate cavity, sealing rings, control cavity and movable central body.

Flow rate is controlled at the first stage. The second stage serves for optimal distribution of gas generation products in all operation modes. The regulator requires a wider range of operating pressures, and the presence of an intermediate cavity between the cascades increases the packing of the structure. To avoid the effect of slag formation on the flow area of the two-stage flow regulator, it is necessary to increase the travel of the central body.

Conclusion

During the course design, the flow controller of the combined rocket engine on aluminum-containing fuel was designed. In particular, the pressure at the control cavity was calculated, the flow section areas at the inlet and at the outlet of the flow regulator were calculated. The dependence of the inlet area on the flow rate of combustion products was calculated with an increase in flow from 0.25 to 0.6, the inlet area decreases from 2.2 * 104m2 to 2 * 105m2.

The project was carried out using modern design automation and engineering analysis using methods recognized and used in the design of propulsion systems. This approach to the design of the engine ensured a fairly high accuracy of the results.

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