Development of Cryogenic engine is essential requirement in order to improve the pay load capability of rocket launching systems. Cryogenic stage is more suitable for the upper stage of the launch vehicle mainly due to the high specific impulse and relatively low structural weight. As the pay load increases a high thrust booster engine is also required for the launch vehicle. Semi cryogenic propulsion is ideally suitable for booster engine, in terms of higher density impulse and low cost and easy handling. LPSC has undertaken the development of Semi Cryo Engine to power the booster stages of India's future launch vehicles. The Engine works on Oxidizer rich staged combustion cycle, using LOX and Isrosene propellant combination. Preburner (PB) and Thrust Chamber (TC) are the major subsystems of the engine. PB produces the hot gases at lower temperature for driving the turbo pump which raises the propellant pressure and TC produces hot gas in the chamber at high temperature which expands through the nozzle for generating thrust. Design of injector and arrangement of injector are critical in the design of pre burner and Thrust chamber so as to admit and meter the propellants into the chamber with proper mixture to ensure complete and stable combustion. The propellants require ignition source for initiating ignition. A mixture of Tri-ethyl Aluminium and Tri-ethyl Boron (TEA/TEB) is used as a source of ignition which is hypergolic with oxygen. In order to understand the behavior of the different systems and technology involved, it is planned to design and realize injector and evaluate the characteristics of its performance during cold flow as well as hot test. The development programme is planned in two phases. Initially Single element pre burner and thrust chamber hardware are realized, cold flow test are carried out and hot test are being done. It is also planned to realize subscale thrust chamber and pre burner as a phase-2 activity to study the behavior of multi element interaction and its performance. A lot of critical technologies are to be developed and demonstrated prior to the development of full scale engine. The characterization of injector elements, performance validation at near operating conditions, Ignition characteristics of hypergolic liquid, validation of material, evaluation of different coating are set for the objectives of the initial phase of tests. This paper discuss the different experimental studies carried out, experimental results and features of hardware, design aspects, cold flow characteristics, hot test result for the initial phase of development and also future plan of action.