This project is to investigate the LPG fuel injection of gases into supersonic flow field. The n... more This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.
ABSTRACT
This project is to investigate the LPG fuel injection of gases into supersonic flow fie... more ABSTRACT
This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.
In this presentation, i just convey my point of work as a handyman in a airline. I worked as a ha... more In this presentation, i just convey my point of work as a handyman in a airline. I worked as a handyman so that what are the works we are doing in the airport and how much it is difficult. I am explaining in this pdf.
This project is to investigate the LPG fuel injection of gases into supersonic flow field. The n... more This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.
ABSTRACT
This project is to investigate the LPG fuel injection of gases into supersonic flow fie... more ABSTRACT
This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.
In this presentation, i just convey my point of work as a handyman in a airline. I worked as a ha... more In this presentation, i just convey my point of work as a handyman in a airline. I worked as a handyman so that what are the works we are doing in the airport and how much it is difficult. I am explaining in this pdf.
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Papers by S PANDIYARAJAN
This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.
Conference Presentations by S PANDIYARAJAN
Talks by S PANDIYARAJAN
Drafts by S PANDIYARAJAN
This project is to investigate the LPG fuel injection of gases into supersonic flow field. The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas (LPG) is injected by varying angles into a supersonic free stream, a dedicated test section and CD nozzle were developed which was attached to the existing duct burner equipment. A set of experiments was performed to validate the numerical results. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In particular, air fuel mixing efficiency measurements obtained by using Schlieren images show that the numerical measured values. The results agree with the literature, and the reference Schlieren images show the associated shock and flow structures that are expected with a jet in cross flow.