Design of heated flow wind tunnel facility for testing small size ramjet engine combustors
This report documents the research studies on the design of a 'high speed heated flow wind tunnel facility', to test a 'Trapped Vortex Concept' (TVC) combustor of a ramjet engine, designed for the DSO National Laboratories, Singapore. The ramjet is to operate at flight s...
| Main Author: | |
|---|---|
| Other Authors: | |
| Format: | Thesis |
| Language: | English |
| Published: |
2015
|
| Subjects: | |
| Online Access: | http://hdl.handle.net/10356/65089 |
| _version_ | 1811681445196857344 |
|---|---|
| author | Panikulam, John Paul |
| author2 | Randy Chue |
| author_facet | Randy Chue Panikulam, John Paul |
| author_sort | Panikulam, John Paul |
| collection | NTU |
| description | This report documents the research studies on the design of a 'high speed heated
flow wind tunnel facility', to test a 'Trapped Vortex Concept' (TVC) combustor of
a ramjet engine, designed for the DSO National Laboratories, Singapore. The ramjet
is to operate at flight speeds of Mach 2.5 to 4.0. A direct-connect wind tunnel is
designed in order to test the ramjet combustor. Combustion testing can be carried
out when the wind tunnel is running. Pebble bed type heaters are used to heat the air
to the required operating conditions.
A thermodynamic cycle analysis was performed on the ramjet engine to estimate air
properties at the combustor inlet. The calculations revealed that even though the
flight is supersonic, the inlet condition to combustor was still subsonic (Mach 0.70
and 0.80 corresponding to flight speed of Mach 2.5 and 4.0 respectively). Hence the
wind tunnel was designed to run at subsonic speeds. A wind tunnel design was
developed to deliver the estimated air properties corresponding to maximum
operating conditions (Mach 0.80), at the combustor inlet. Specifications for
machinery such as compressor, air storage tank, pebble bed heater, etc were
estimated such as to provide the calculated operating conditions of the wind tunnel.
Finally pressure drop calculations were performed on the pipelines and fittings for
pipe line sizing of the facility. |
| first_indexed | 2024-10-01T03:41:03Z |
| format | Thesis |
| id | ntu-10356/65089 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T03:41:03Z |
| publishDate | 2015 |
| record_format | dspace |
| spelling | ntu-10356/650892023-03-11T18:09:35Z Design of heated flow wind tunnel facility for testing small size ramjet engine combustors Panikulam, John Paul Randy Chue School of Mechanical and Aerospace Engineering DRNTU::Engineering::Manufacturing This report documents the research studies on the design of a 'high speed heated flow wind tunnel facility', to test a 'Trapped Vortex Concept' (TVC) combustor of a ramjet engine, designed for the DSO National Laboratories, Singapore. The ramjet is to operate at flight speeds of Mach 2.5 to 4.0. A direct-connect wind tunnel is designed in order to test the ramjet combustor. Combustion testing can be carried out when the wind tunnel is running. Pebble bed type heaters are used to heat the air to the required operating conditions. A thermodynamic cycle analysis was performed on the ramjet engine to estimate air properties at the combustor inlet. The calculations revealed that even though the flight is supersonic, the inlet condition to combustor was still subsonic (Mach 0.70 and 0.80 corresponding to flight speed of Mach 2.5 and 4.0 respectively). Hence the wind tunnel was designed to run at subsonic speeds. A wind tunnel design was developed to deliver the estimated air properties corresponding to maximum operating conditions (Mach 0.80), at the combustor inlet. Specifications for machinery such as compressor, air storage tank, pebble bed heater, etc were estimated such as to provide the calculated operating conditions of the wind tunnel. Finally pressure drop calculations were performed on the pipelines and fittings for pipe line sizing of the facility. Master of Science (Manufacturing Systems and Engineering) 2015-06-15T01:31:49Z 2015-06-15T01:31:49Z 2014 2014 Thesis http://hdl.handle.net/10356/65089 en 91 p. application/pdf |
| spellingShingle | DRNTU::Engineering::Manufacturing Panikulam, John Paul Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title | Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title_full | Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title_fullStr | Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title_full_unstemmed | Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title_short | Design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| title_sort | design of heated flow wind tunnel facility for testing small size ramjet engine combustors |
| topic | DRNTU::Engineering::Manufacturing |
| url | http://hdl.handle.net/10356/65089 |
| work_keys_str_mv | AT panikulamjohnpaul designofheatedflowwindtunnelfacilityfortestingsmallsizeramjetenginecombustors |