SCE-200 : 🇮🇳's First Semi-Cryogenic Engine

Updated: Jun 5, 2023

Introduction:-

SCE-200 also known as Semi-Cryogenic Engine - 200 ( Tonne Thrust )
Developed by Liquid Propulsions Systems Centre ( LPSC ), Thiruvananthapuram, Kerala, India. ( Part of ISRO )
ISRO's 2000kN Semi-Cryogenic Engine will use Liquid Oxygen (LOX) and ISROSENE ( A Green propellant for use in future rocket & satellite propulsion systems, Basically rocket grade version of kerosene ) More About it Here:- ISROSENE LINK
It's an Oxidizer Rich Staged Combustion Cycle Engine that will be Used to Power ISRO's Future Medium and Heavy Lift Launch Vehicles, which help ISRO to deliver more payload into Space.
It will first Replace the 2 VIKAS Engines of the LVM3 Core Stage with 1 SCE-200 Engine. Even that New 1 Engine can Produce more thrust than the Previous 2 Engines. Which Help's in the Increase Payload Capacity of the LVM3 Launch Vehicle.
The engine however will not be the part of first flight of Gaganyaan, India's first manned mission to space given timelines and schedules
There are speculations that this engine will be used in ISRO's Future Next Generation Launch Vehicle (NGLV) Previously termed as Unified Launch Vehicle (ULV)
In 2009, the SCE-200 program was approved for ₹1798 crore (US$230 Million) and the program to develop a 2 MN class or 2000 kN Class main engine began

Designer of the Engine	LPSC, Thiruvananthapuram (ISRO)
Development years	from 2005
Engine Type	Oxidizer Rich Stage Combustion Cycle Liquid rocket engine
Status	Under Development
Propellant	ISROSENE + LOX
Oxidiser/Fuel Ratio (O/F)	2.65
Chamber Pressure	180 Bar or 18 MPa (2,600 psi)
Thrust in vacuum	2,030 kN ( 203 Tonne )
Thrust at Sea-Level	1,820 kN ( 182 Tonne )
Specific impulse (Isp) in Vaccum	335 s (3.29 km/s)
Specific impulse (Isp) at Sea-Level	299 s (2.93 km/s)
Throttle	60% to 105%
Pumps	3 Turbo Pumps 1. Main Turbopump 2. Fuel Booster Turbopump 3. Oxidiser Booster Turbopump
Nozzle Expansion Ratio	Will be Updated
Burn time	Will be Updated
Length	Will be Updated
Engine Dry Weight	2,700 kg
Diameter	Will be Updated
Combustion Camber	Single Combustion Chamber
Thrust to weight ratio	Will be Updated
Manufacturer	HAL and Godrej & Boyce
Used on	NGLV ( formerly ULV )

ISRO had a Newly Commissioned Semicryogenic Integrated Engine & Stage Test facility at the ISRO Propulsion Complex (IPRC), Mahendragiri.
The newly established test facility at IPRC, Mahendragiri, is capable of testing semi-cryogenic engines up to 2600 kN thrust and will support the subsequent testing and qualification of the fully integrated Semicryogenic engine and stage.

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