A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion

Berlin Huang, Hsiao-Feng Yuan, Yu Ta Chen, Yu Hsiang Su

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

Abstract

Green (low toxicity) liquid rocket propellants have become attractive in recent years due to the features of the low cost and less environmental impact. However, the green propellants, such as kerosene/H2O2, usually have different operational conditions (i.e. relatively high O/F ratio) compared to conventional propellants because of their chemical properties. In this research, a new concept of the two-stage impinging type injector (O-F-F-O) is adopted for investigating the spray mixing at high O/F ratios between 3.75 and 6.25. The impinging distance, jet velocity and impinging angle for the two-stage impinging type injector are design parameters examined, where the impinging angle is more effective at spray atomization and droplet distribution. The PLIF technique is used to measure the droplet distribution so as to identify the spray characteristics. In order to simplify the development process of the injector, the predicted mixture ratio distribution from the individual fuel (F-F) and oxidizer (O-O) sprays by overlapping their averaged images is used to compare with the actual distribution from the two-stage impinging spray (O-F-F-O). At a constant total mass flow rate, results indicate that tendencies towards the variations of the average characteristic velocity (C*) with increasing O/F ratios are similar for outcomes of the prediction and actual measurement. Also, there is obvious flow fields interaction between the fuel and oxidizer sprays and coordinating their relative intensities of sprays well can optimize the mixture ratio distribution of the two-stage impinging spray. Better mixing occurs when the fuel and oxidizer sprays have more similar and uniform distributions.

Original languageEnglish
Title of host publication51st AIAA/SAE/ASEE Joint Propulsion Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103216
Publication statusPublished - 2015
Event51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015 - Orlando, United States
Duration: 2015 Jul 272015 Jul 29

Other

Other51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015
CountryUnited States
CityOrlando
Period15-07-2715-07-29

Fingerprint

Propellants
Rockets
Propulsion
Kerosene
Atomization
Chemical properties
Environmental impact
Toxicity
Flow fields
Flow rate
Liquids
Costs

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Huang, B., Yuan, H-F., Chen, Y. T., & Su, Y. H. (2015). A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion. In 51st AIAA/SAE/ASEE Joint Propulsion Conference American Institute of Aeronautics and Astronautics Inc, AIAA.
Huang, Berlin ; Yuan, Hsiao-Feng ; Chen, Yu Ta ; Su, Yu Hsiang. / A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion. 51st AIAA/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015.
@inproceedings{0ba555500e384835898d77b64c616377,
title = "A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion",
abstract = "Green (low toxicity) liquid rocket propellants have become attractive in recent years due to the features of the low cost and less environmental impact. However, the green propellants, such as kerosene/H2O2, usually have different operational conditions (i.e. relatively high O/F ratio) compared to conventional propellants because of their chemical properties. In this research, a new concept of the two-stage impinging type injector (O-F-F-O) is adopted for investigating the spray mixing at high O/F ratios between 3.75 and 6.25. The impinging distance, jet velocity and impinging angle for the two-stage impinging type injector are design parameters examined, where the impinging angle is more effective at spray atomization and droplet distribution. The PLIF technique is used to measure the droplet distribution so as to identify the spray characteristics. In order to simplify the development process of the injector, the predicted mixture ratio distribution from the individual fuel (F-F) and oxidizer (O-O) sprays by overlapping their averaged images is used to compare with the actual distribution from the two-stage impinging spray (O-F-F-O). At a constant total mass flow rate, results indicate that tendencies towards the variations of the average characteristic velocity (C*) with increasing O/F ratios are similar for outcomes of the prediction and actual measurement. Also, there is obvious flow fields interaction between the fuel and oxidizer sprays and coordinating their relative intensities of sprays well can optimize the mixture ratio distribution of the two-stage impinging spray. Better mixing occurs when the fuel and oxidizer sprays have more similar and uniform distributions.",
author = "Berlin Huang and Hsiao-Feng Yuan and Chen, {Yu Ta} and Su, {Yu Hsiang}",
year = "2015",
language = "English",
isbn = "9781624103216",
booktitle = "51st AIAA/SAE/ASEE Joint Propulsion Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

}

Huang, B, Yuan, H-F, Chen, YT & Su, YH 2015, A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion. in 51st AIAA/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015, Orlando, United States, 15-07-27.

A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion. / Huang, Berlin; Yuan, Hsiao-Feng; Chen, Yu Ta; Su, Yu Hsiang.

51st AIAA/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015.

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

TY - GEN

T1 - A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion

AU - Huang, Berlin

AU - Yuan, Hsiao-Feng

AU - Chen, Yu Ta

AU - Su, Yu Hsiang

PY - 2015

Y1 - 2015

N2 - Green (low toxicity) liquid rocket propellants have become attractive in recent years due to the features of the low cost and less environmental impact. However, the green propellants, such as kerosene/H2O2, usually have different operational conditions (i.e. relatively high O/F ratio) compared to conventional propellants because of their chemical properties. In this research, a new concept of the two-stage impinging type injector (O-F-F-O) is adopted for investigating the spray mixing at high O/F ratios between 3.75 and 6.25. The impinging distance, jet velocity and impinging angle for the two-stage impinging type injector are design parameters examined, where the impinging angle is more effective at spray atomization and droplet distribution. The PLIF technique is used to measure the droplet distribution so as to identify the spray characteristics. In order to simplify the development process of the injector, the predicted mixture ratio distribution from the individual fuel (F-F) and oxidizer (O-O) sprays by overlapping their averaged images is used to compare with the actual distribution from the two-stage impinging spray (O-F-F-O). At a constant total mass flow rate, results indicate that tendencies towards the variations of the average characteristic velocity (C*) with increasing O/F ratios are similar for outcomes of the prediction and actual measurement. Also, there is obvious flow fields interaction between the fuel and oxidizer sprays and coordinating their relative intensities of sprays well can optimize the mixture ratio distribution of the two-stage impinging spray. Better mixing occurs when the fuel and oxidizer sprays have more similar and uniform distributions.

AB - Green (low toxicity) liquid rocket propellants have become attractive in recent years due to the features of the low cost and less environmental impact. However, the green propellants, such as kerosene/H2O2, usually have different operational conditions (i.e. relatively high O/F ratio) compared to conventional propellants because of their chemical properties. In this research, a new concept of the two-stage impinging type injector (O-F-F-O) is adopted for investigating the spray mixing at high O/F ratios between 3.75 and 6.25. The impinging distance, jet velocity and impinging angle for the two-stage impinging type injector are design parameters examined, where the impinging angle is more effective at spray atomization and droplet distribution. The PLIF technique is used to measure the droplet distribution so as to identify the spray characteristics. In order to simplify the development process of the injector, the predicted mixture ratio distribution from the individual fuel (F-F) and oxidizer (O-O) sprays by overlapping their averaged images is used to compare with the actual distribution from the two-stage impinging spray (O-F-F-O). At a constant total mass flow rate, results indicate that tendencies towards the variations of the average characteristic velocity (C*) with increasing O/F ratios are similar for outcomes of the prediction and actual measurement. Also, there is obvious flow fields interaction between the fuel and oxidizer sprays and coordinating their relative intensities of sprays well can optimize the mixture ratio distribution of the two-stage impinging spray. Better mixing occurs when the fuel and oxidizer sprays have more similar and uniform distributions.

UR - http://www.scopus.com/inward/record.url?scp=84946033602&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84946033602&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781624103216

BT - 51st AIAA/SAE/ASEE Joint Propulsion Conference

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -

Huang B, Yuan H-F, Chen YT, Su YH. A cold-flow experimental observation of the two-stage impinging type injector for rocket propulsion. In 51st AIAA/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 2015