LPSC, Godrej Aerospace and other propulsion system makers in India

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Thread to discuss, summarise and enlist existing and future rocket engines, boosters and new propulsion systems except SSLV stages and DMRJ/Scramjets.
SSLV' stages will remain at SSLV thread.

I'm wondering if @porky_kicker can help to create a new thread on DMRJ.

Also, I'm going to let this one thread remain for Kerosene, Methane and HTPB engines. If it becomes messy, I will split it.
 
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Design and Analysis of a Methane Pump for 10 Ton Class Rocket Engine
Nayak, Soumya Ranjan (2017) Design and Analysis of a Methane Pump for 10 Ton Class Rocket Engine. MTech thesis.
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Abstract
In rocket propulsion, weight has a vital role on efficiency and cost of the program. Since fuel, oxidiser and delivery system contribute a major share of the total weight; so it is desirable to design an efficient fuel delivery system as well as proper choice of fuel. Methane is being considered as the next generation rocket fuel for its certain advantages over liquid hydrogen and kerosene. Pump-fed system is a well-established preferable fuel delivery system as compared to pressure-fed system. To obtain a reduced size of pump it is necessary to run the device at high rpm (more than 10,000rpm). For this high speed it is not possible to run the pump with electric motor or generator. This leaves turbine as a suitable alternative for primemover. Hence pump-fed system is commonly known as turbo-pump system; as it consists of turbine and pump. Pump gives the necessary pressure rise to the fuel and oxidiser while turbine acts as the prime-mover. The present work is limited to design and analysis of the pump part alone. Although pump-fed system has been successfully designed for various propellants, but the research is limited and new for methane as working fluid. Centrifugal pump is preferred to other kind of pumps because of its compact size for a given head rise and a larger throttling range. A high speed impeller demands for high inlet pressure to meet the NPSH requirement to avoid cavitation. Increasing the storage pressure of propellant will demand for a thicker tank and hence higher structural mass, which is undesirable for high performance. Hence an inducer is necessary before impeller to raise the propellant pressure from storage value to required NPSH value at inlet of impeller. The impeller is followed by a volute and diffuser assembly which is intended to give a directional flow to the fluid and convert velocity head into pressure head. The focus of the work is to determine the throttling range, pressure distribution, velocity distribution and performance evaluation for the assembly.
Item Type:Thesis (MTech)
Uncontrolled Keywords:Inducer; Throttle; NPSH; Propulsion
Subjects:Engineering and Technology > Mechanical Engineering > Cryogenics
Divisions:Engineering and Technology > Department of Mechanical Engineering
ID Code:8980
Deposited By:Mr. Kshirod Das
Deposited On:25 Apr 2018 11:31
Last Modified:25 Apr 2018 11:31
Supervisor(s):Sahoo, Ranjit Kumar and Panigrahi, Sridhar
 

Varun2002

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Very clear chronicle of developments. One little bit of puzzlement- For Jan 2019 and April 2019 respectively, there is a mention of 'first propellant tank realised'for the P4 and P2 stages. What does this mean, that the specific material for constructing the tanks were used for the first time, or that these were the first propellant tanks made in India( please say it isn't so), and that before these, the tanks were mostly if not wholly imported? That would be hard to believe. Clarity sought! :)
 
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Very clear chronicle of developments. One little bit of puzzlement- For Jan 2019 and April 2019 respectively, there is a mention of 'first propellant tank realised'for the P4 and P2 stages. What does this mean, that the specific material for constructing the tanks were used for the first time, or that these were the first propellant tanks made in India( please say it isn't so), and that before these, the tanks were mostly if not wholly imported? That would be hard to believe. Clarity sought! :)
In January 2019, we had first propellant tank made of Aluminium alloy for PSLV. In April 2019, it was first time that BrahMos Aerospace delivered a tank (private vendor added).
 
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Enlisting existing systems;
Hydrazine/Nitrogen oxides based fuels
Vikas 2 (GSLV I) - 600-680 kN
Vikas 2B (GSLV II) - 678-766 kN
Vikas X (GSLV III) - 757-839 kN
Vikas 4 (GSLV I, PSLV) - 725 (Upper stage only)
Vikas 4B (GSLV I, PSLV) - 725 (Upper stage only)
Cryo engines:
Liquid Hydrogen + Oxygen
CE-7.5 (GSLV II) - 73.5 to 82 kN
CE-20 (GSLV III) - 200 kN

Upcoming cryo:
Kerosene + Liquid Oxygen
SCE-200 (GSLV III, HLV, SHLV, UMLV): 1820-2030kN
(Will be India's monster engine).
 

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