Journal of Mechanical Science and Technology, 2015
Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic M... more Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers. The surface measurements were used to analyze the internal flow field of the engine. The heat flux measurements revealed the regions of peak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant area duct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shock waves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for a possible fuelled operation in future.
Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated thro... more Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated through Reynolds analogy, using measured wall heat transfer rates, in a shock tunnel at a hypersonic Mach number of 8. The study has been carried out without fuel injection and at zero degree angle of incidence of the model with the freestream. The heat transfer rate measurements were carried out on the upper and lower internal surfaces of the engine employing fast response E-type thermocouples. Application of Reynolds analogy to the wall heat transfer rates yielded the skin friction coefficient, through which the viscous drag on the surfaces could be determined. The measurements predict the salient features of the flow field of the model and are a novel reference on the data to the researchers working in the area of slender-body, hypersonic aerothermodynamics.
Gas turbine has been making impact in variety of applications in recent time. With development of... more Gas turbine has been making impact in variety of applications in recent time. With development of the gas turbine it has become critical to get accurate information of its behavior at the design stage. Customers demand guarantees of the response rate at the proposal stage. ...
Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic M... more Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers. The surface measurements were used to analyze the internal flow field of the engine. The heat flux measurements revealed the regions of peak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant area duct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shock waves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for a possible fuelled operation in future.
Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated thro... more Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated through Reynolds analogy, using measured wall heat transfer rates, in a shock tunnel at a hypersonic Mach number of 8. The study has been carried out without fuel injection and at zero degree angle of incidence of the model with the freestream. The heat transfer rate measurements were carried out on the upper and lower internal surfaces of the engine employing fast response E-type thermocouples. Application of Reynolds analogy to the wall heat transfer rates yielded the skin friction coefficient, through which the viscous drag on the surfaces could be determined. The measurements predict the salient features of the flow field of the model and are a novel reference on the data to the researchers working in the area of slender-body, hypersonic aerothermodynamics.
Gas turbine has been making impact in variety of applications in recent time. With development of... more Gas turbine has been making impact in variety of applications in recent time. With development of the gas turbine it has become critical to get accurate information of its behavior at the design stage. Customers demand guarantees of the response rate at the proposal stage. Transient performance deals with the operating regime where engine performance parameters are changing with time. The dynamic response of the gas turbine cannot be investigated experimentally until the program is well advanced. The simulation techniques, if used, using mathematical models permit the investigation of the dynamic behavior at early stage of design. This also helps in designing control systems for the gas turbines. The paper deals with the development of an aero-thermodynamic model for a single-spool turbojet engine. The mathematical model of the gas turbine has been developed and analysis has been carried out using software.
Journal of Mechanical Science and Technology, 2015
Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic M... more Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers. The surface measurements were used to analyze the internal flow field of the engine. The heat flux measurements revealed the regions of peak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant area duct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shock waves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for a possible fuelled operation in future.
Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated thro... more Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated through Reynolds analogy, using measured wall heat transfer rates, in a shock tunnel at a hypersonic Mach number of 8. The study has been carried out without fuel injection and at zero degree angle of incidence of the model with the freestream. The heat transfer rate measurements were carried out on the upper and lower internal surfaces of the engine employing fast response E-type thermocouples. Application of Reynolds analogy to the wall heat transfer rates yielded the skin friction coefficient, through which the viscous drag on the surfaces could be determined. The measurements predict the salient features of the flow field of the model and are a novel reference on the data to the researchers working in the area of slender-body, hypersonic aerothermodynamics.
Gas turbine has been making impact in variety of applications in recent time. With development of... more Gas turbine has been making impact in variety of applications in recent time. With development of the gas turbine it has become critical to get accurate information of its behavior at the design stage. Customers demand guarantees of the response rate at the proposal stage. ...
Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic M... more Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers. The surface measurements were used to analyze the internal flow field of the engine. The heat flux measurements revealed the regions of peak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant area duct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shock waves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for a possible fuelled operation in future.
Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated thro... more Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated through Reynolds analogy, using measured wall heat transfer rates, in a shock tunnel at a hypersonic Mach number of 8. The study has been carried out without fuel injection and at zero degree angle of incidence of the model with the freestream. The heat transfer rate measurements were carried out on the upper and lower internal surfaces of the engine employing fast response E-type thermocouples. Application of Reynolds analogy to the wall heat transfer rates yielded the skin friction coefficient, through which the viscous drag on the surfaces could be determined. The measurements predict the salient features of the flow field of the model and are a novel reference on the data to the researchers working in the area of slender-body, hypersonic aerothermodynamics.
Gas turbine has been making impact in variety of applications in recent time. With development of... more Gas turbine has been making impact in variety of applications in recent time. With development of the gas turbine it has become critical to get accurate information of its behavior at the design stage. Customers demand guarantees of the response rate at the proposal stage. Transient performance deals with the operating regime where engine performance parameters are changing with time. The dynamic response of the gas turbine cannot be investigated experimentally until the program is well advanced. The simulation techniques, if used, using mathematical models permit the investigation of the dynamic behavior at early stage of design. This also helps in designing control systems for the gas turbines. The paper deals with the development of an aero-thermodynamic model for a single-spool turbojet engine. The mathematical model of the gas turbine has been developed and analysis has been carried out using software.
Uploads
Papers by Jigar Sura