Design of turbo pump unit for the engine of the first stage of the rocket based on the analogue RD107

Contents

1. Assignment and analysis of the course project

2. Propulsion system diagram

3. Physicochemical characteristics of fuel components

3.1 Asymmetric dimethylhydrazine

3.2 Nitric acid

3.3 Fuel steam

4. Work of the ASG

5. Define initial data for TPA calculation

5.1. Selection of YY parameters

5.2. Determination of mass expenditures in the COP

5.3. Balance sheet settlement

6. CALCULATION OF OXIDIZER PUMP

6.1 Determination of pump output parameters

6.2 Determination of angular velocity

6.3 Calculation of screw and inlet to centrifugal wheel

6.4 Matching of screw parameters at output and DBK parameters at input

6.5 Calibration cavitation calculation

6.6 Centrifugal Wheel Sizing

6.7 Supply calculation

6.8 Calculation of diversion

6.9 Calculation of pump losses, power and efficiency

6.10 Calculation of seals

7 FUEL PUMP CALCULATION

7.1 Determination of pump output parameters

7.2 Calculation of screw and inlet to pulp mill

7.3 Matching of screw parameters at output and DBK parameters at input

7.4 Verification cavitation calculation

7.5 Mill sizing

7.6 Supply calculation

7.7 Calculation of diversion

7.8 Calculation of pump losses, power and efficiency

7.9 Calculation of seals

8. Turbine Calculation

8.1 Determination of required gas flow rate

8.2 Flow parameters in axial clearance

8.3 Determination of optimal height of wheel blades

8.4 Sizing of nozzle unit consisting of conical nozzles

8.5 Determination of wheel grille parameters

8.6 Determination of flow parameters at wheel outlet

8.7 Determination of turbine operation, power and efficiency

9. List of literature

Assignment and analysis of the course project

Design a turbopump unit (TPA) for the engine of the first stage of the rocket based on the analogue RD107. Diagram without afterburning of generator gases (open) having the following parameters:

Thrust in the void - Rp = 1.1 MN;

Pressure in the combustion chamber - Rks = 8.0 MPas;

Nozzle shear pressure - Pa = 0.05 MPa;

Operating time - t∑ = 140c.

Fuel components:

Oxidizer - AT;

Fuel - NDMG.

One-time launch. Works without interruption. Tanks are pressurized due to GAD. To ensure maximum flight range, it is advisable to use a FDS that will allow high speed at the end of the active section. To ensure stable operation mode and for maximum use of fuel energy going to the turbine and being thrown overboard, install MCS on GG fuel line, and flow rate through GG is controlled using RCS regulator on GG oxidizer line.

Propulsion system diagram

The nature of the solution of pneumohydraulic systems of the propulsion system is determined by the general peculiarities of the chamber power supply with fuel components: a pump-type supply system without afterburning of the reducing generator gas. The use of reducing gas is justified by the fact that the permissible temperature of such gas for the turbine blades is higher than the oxidizing gas, and this gas has a large gas constant. Consequently, the adiabat operation of the gas used to drive the reduction turbines is greater than that of the oxidizing ones, which is advantageous in the energy balance of this fuel supply system.

According to this scheme, the reducing gas after the turbine is sent to the environment. The disadvantage of such a scheme is that chemical energy irretrievably disappears. Although it is relatively easier to constructively implement the scheme without afterburning than the scheme with afterburning. It is also necessary to ensure a reliable separation of the turbine and the oxidizer pump, since the gas is reducing. This is achieved by installing thermally insulating gaskets.

The advantage of circuits with self-igniting components is that it does not need any starting systems, but for more reliable start-up, we will use a solid fuel gas generator (THG) located in front of the turbine to pre-spin the turbine and cut the membrane valves. In order to use self-igniting components in an open circuit, it is necessary to organize a special starting line for supplying components to the gas generator, through which at a low supply pressure, their flow rate would be higher.

The use of the AT + NDMG fuel pair contributes to the design of the remote control. Self-igniting components therefore the organization of process of burning in the combustion chamber (CC) and gas generators, does not require additional measures for providing the reliable and simple ignition system.

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