Velocity field in secondary combustor of ejector-jet

Kiyoshi Nojima, Toshinori Kouchi, Goro Masuya, Sadatake Tomioka

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed.

Original languageEnglish
Title of host publication18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Publication statusPublished - 2012
Event18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 - Tours, France
Duration: Sep 24 2012Sep 28 2012

Other

Other18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
CountryFrance
CityTours
Period9/24/129/28/12

Fingerprint

ejectors
combustion chambers
Combustors
velocity distribution
Rockets
Velocity distribution
combustion
Rocket nozzles
Engines
engines
engine
rocket exhaust
rocket nozzles
Compressed air
Sea level
compressed air
Velocity measurement
pressure chambers
Helium
cold air

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Nojima, K., Kouchi, T., Masuya, G., & Tomioka, S. (2012). Velocity field in secondary combustor of ejector-jet. In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012

Velocity field in secondary combustor of ejector-jet. / Nojima, Kiyoshi; Kouchi, Toshinori; Masuya, Goro; Tomioka, Sadatake.

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 2012.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Nojima, K, Kouchi, T, Masuya, G & Tomioka, S 2012, Velocity field in secondary combustor of ejector-jet. in 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012, Tours, France, 9/24/12.
Nojima K, Kouchi T, Masuya G, Tomioka S. Velocity field in secondary combustor of ejector-jet. In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 2012
Nojima, Kiyoshi ; Kouchi, Toshinori ; Masuya, Goro ; Tomioka, Sadatake. / Velocity field in secondary combustor of ejector-jet. 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 2012.
@inproceedings{eeb757d355304b35abc8e62ac1e9ffc2,
title = "Velocity field in secondary combustor of ejector-jet",
abstract = "Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed.",
author = "Kiyoshi Nojima and Toshinori Kouchi and Goro Masuya and Sadatake Tomioka",
year = "2012",
language = "English",
isbn = "9781600869310",
booktitle = "18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012",

}

TY - GEN

T1 - Velocity field in secondary combustor of ejector-jet

AU - Nojima, Kiyoshi

AU - Kouchi, Toshinori

AU - Masuya, Goro

AU - Tomioka, Sadatake

PY - 2012

Y1 - 2012

N2 - Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed.

AB - Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed.

UR - http://www.scopus.com/inward/record.url?scp=84881011537&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84881011537&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781600869310

BT - 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012

ER -