GasTurbineEngine_Report.pdf - Department of Aerospace Engineering Indian Institute of Technology Bombay Propulsion Lab Report Study of mini Gas Turbine

GasTurbineEngine_Report.pdf - Department of Aerospace...

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Department of Aerospace Engineering Indian Institute of Technology, Bombay Propulsion Lab Report Study of mini Gas Turbine Engine Aerospace Propulsion Laboratory AE607 Submitted By Kandimalla Chacha Srihari 183010034 Date Performed: 9 th July, 2018
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OBJECTIVE: 1. To understand the operation of gas turbine engine which operates on BRAYTON cycle. 2. To take observation & perform relevant calculation in order to successfully understand the relations between relevant performance parameters. APPARATUS: 1. SR-30 GAS TURBINE ENGINE 2. Data Acquisition Chamber THEORY: A pure turbojet, the SR-30 is representative of all straight jet engines in which combustion results in an expanding gas that is sufficiently capable of producing useful work and propulsive thrust. Consisting of a centrifugal flow compressor, annular combustor and axial flow power turbine, the SR-30 engine is typical of the gas generator core found in turbofan, turboprop and turbo-shaft gas turbine engines, which are typically used for aircraft and marine propulsion, as well as stationary and industrial power generation. ENGINE SETUP:
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RPM Tachometer Generator : (Displayed on Panel as RPM and Data Acquisition Screen). P1 : Compressor Inlet Pressure (Displayed on Data Acquisition Screen) T1 : Compressor Inlet Temperature (Displayed on Data Acquisition Screen) P2 : Compressor Exit Pressure (Displayed on Data Acquisition Screen) T2 : Compressor Exit Temperature (Displayed on Data Acquisition Screen) P3
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