NDLI: An experimental study on transverse hydrogen gas injection into Mach 1.8 airflow channel : The 2nd report: Tandem circular injectors

Content Provider	Springer Nature Link
Author	Nagashima, T. guchi, S. Itoh, H. Kotani, Y.
Copyright Year	1992
Abstract	Hydrogen gas has been injected transversely into Mach 1.8 airflow between parallel channel walls from two circular sonic injectors which were mounted flush and placed in tandem along the centre line of the bottom wall plate of a test section. Both cold and hot airflow conditions, i.e. atmospheric and heated to max.1460K total temperature, were tested. In the cold flow experiments, detailed measurements were successful and the tandem injection resulted in a marked difference from the single injection with respect to the pattern of shock waves and the distribution of pressure and hydrogen concentration near the injector region. Upon changing the injection pressure ratio between the two injectors, it has been revealed that a prior injection upstream of the main injection would be beneficial in terms of the total pressure loss in the airflow and the hydrogen concentration near the injector region while maintaining the mixing performance. In general, the flow features showed little difference as the airflow temperature was raised until hydrogen burning was observed, whence the results became inevitably less quantitative. Against the expectation from the cold flow tests, a prior injection of cold hydrogen has resulted in quenching the main injector flame.
Starting Page	218
Ending Page	225
Page Count	8
File Format	PDF
ISSN	10032169
Journal	Journal of Thermal Science
Volume Number	6
Issue Number	3
e-ISSN	1993033X
Language	English
Publisher	Science Press
Publisher Date	1992-01-01
Publisher Place	Beijing
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	SCRamjet supersonic combustion hydrogen transverse injection Mechanics, Fluids, Thermodynamics Engineering Fluid Dynamics Engineering Thermodynamics, Transport Phenomena
Content Type	Text
Resource Type	Article
Subject	Condensed Matter Physics

Sl.	Authority	Responsibilities	Communication Details
1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
3	National Digital Library of India Office, Indian Institute of Technology Kharagpur	The administrative and infrastructural headquarters of the project	Dr. B. Sutradhar bsutra@ndl.gov.in
4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
5	Website/Portal (Helpdesk)	Queries regarding NDLI and its services	support@ndl.gov.in
6	Contents and Copyright Issues	Queries related to content curation and copyright issues	content@ndl.gov.in
7	National Digital Library of India Club (NDLI Club)	Queries related to NDLI Club formation, support, user awareness program, seminar/symposium, collaboration, social media, promotion, and outreach	clubsupport@ndl.gov.in
8	Digital Preservation Centre (DPC)	Assistance with digitizing and archiving copyright-free printed books	dpc@ndl.gov.in
9	IDR Setup or Support	Queries related to establishment and support of Institutional Digital Repository (IDR) and IDR workshops	idr@ndl.gov.in

An experimental study on transverse hydrogen gas injection into mach 1.8 airflow channel : The 1st report: Single circular injector

The effect of injection angle on mixing and flame holding in supersonic combustor

The Two-Dimensional supersonic flow and mixing with a perpendicular injection in a Scramjet Combustor

Self-induced oscillation of supersonic jet during impingement on cylindrical body

Temperature distribution on inclined plate caused by interaction with supersonic jet

Numerical study for hysteresis phenomena of shock wave reflection in overexpanded axisymmetric supersonic jet

Numerical simulation of tip leakage vortex effect on hydrogen-combustion flow around 3D turbine blade

Numerical Simulation of a Hydrogen Fueled Scramjet Combustor at Mach 1.5 Using Strut Injectors at Mach 2.47 Air Speed

3D computation of hydrogen-fueled combustion around turbine blade-effect of arrangement of injector holes-

An experimental study on transverse hydrogen gas injection into Mach 1.8 airflow channel : The 2nd report: Tandem circular injectors

Similar Documents

An experimental study on transverse hydrogen gas injection into mach 1.8 airflow channel : The 1st report: Single circular injector

The effect of injection angle on mixing and flame holding in supersonic combustor

The Two-Dimensional supersonic flow and mixing with a perpendicular injection in a Scramjet Combustor

Self-induced oscillation of supersonic jet during impingement on cylindrical body

Temperature distribution on inclined plate caused by interaction with supersonic jet

Numerical study for hysteresis phenomena of shock wave reflection in overexpanded axisymmetric supersonic jet

Numerical simulation of tip leakage vortex effect on hydrogen-combustion flow around 3D turbine blade

Numerical Simulation of a Hydrogen Fueled Scramjet Combustor at Mach 1.5 Using Strut Injectors at Mach 2.47 Air Speed

3D computation of hydrogen-fueled combustion around turbine blade-effect of arrangement of injector holes-

An experimental study on transverse hydrogen gas injection into Mach 1.8 airflow channel : The 2nd report: Tandem circular injectors