Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor

Jeffrey David Moore, Robert B. Wehrman, Peter J. Ferrara, Kenneth K. Kuo

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

4 Citations (Scopus)

Abstract

Fin-slot propellent grains have been used in a variety of solid rocket propulsion systems. Advantages of fin-slot propellant grains include: a constant total burning surface area and thrust level, large burning surface area, large free volume, and greater reliability for ignition. It is known that the fin-slot region has confined space and a complex geometry and the influence of the igniter jet has a profound effect on the flow-field re-circulating patterns, due to its impingement angle, degree of under-expansion, and strength of the induced vortex. In order to accurately predict the overall ignition transient for the reusable solid rocket motors (RSRM) of the Space Shuttle booster with head-end fin slots, it is necessary to have the knowledge of the energy transfer rates in the fin-slot region. An approximate 1:10th scale pie-shaped fin-slot motor was designed to simulate the first segment of the fin-slot RSRM and to perform diagnostic measurements for studying the flow and heat transfer behavior on the exposed propellant surface. The simulation motor consisted of a single, inert triangular fin section mounted in a horizontal, 2-D axisymmetric stainless steel chamber with an observation window. Opposite to this flow-visualization window was an array of 36 flushmounted heat-flux gauges installed on a diagnostic panel in a perpendicular orientation to detect the local temperature rise rates at representative regions of the fin-slot propellant surface. Clean air was compressed in a storage tank and allowed to pass through a heated blow-down wind tunnel for supplying hot airflow through the igniter section and into the fin-slot region at multiple temperature levels, simulating the hot gas products from the igniter. Data from the direct discharge of a live igniter onto an inert fin-slot propellant sample were also collected for comparison with the hot-air heat transfer experiments. Results were used to develop a correlation between the internal flow-field and heat-transfer within the fin-slot region. The heat-transfer rates evaluated from this correlation matched the measured data trend with in the experimental error.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Pages4456-4467
Number of pages12
Volume6
StatePublished - 2006
EventAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference - Sacramento, CA, United States
Duration: Jul 9 2006Jul 12 2006

Other

OtherAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
CountryUnited States
CitySacramento, CA
Period7/9/067/12/06

Fingerprint

internal flow
Rocket engines
fins
flux measurement
Propellants
rockets
slots
flow field
heat flux
Heat flux
Flow fields
flow distribution
heat transfer
Heat transfer
igniters
Ignition
surface area
Fins (heat exchange)
Space shuttles
Free volume

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Energy(all)
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

Cite this

Moore, J. D., Wehrman, R. B., Ferrara, P. J., & Kuo, K. K. (2006). Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor. In Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference (Vol. 6, pp. 4456-4467)
Moore, Jeffrey David ; Wehrman, Robert B. ; Ferrara, Peter J. ; Kuo, Kenneth K. / Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor. Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference. Vol. 6 2006. pp. 4456-4467
@inproceedings{523b4bf5640c4a6a8e4cfef6bdc7212d,
title = "Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor",
abstract = "Fin-slot propellent grains have been used in a variety of solid rocket propulsion systems. Advantages of fin-slot propellant grains include: a constant total burning surface area and thrust level, large burning surface area, large free volume, and greater reliability for ignition. It is known that the fin-slot region has confined space and a complex geometry and the influence of the igniter jet has a profound effect on the flow-field re-circulating patterns, due to its impingement angle, degree of under-expansion, and strength of the induced vortex. In order to accurately predict the overall ignition transient for the reusable solid rocket motors (RSRM) of the Space Shuttle booster with head-end fin slots, it is necessary to have the knowledge of the energy transfer rates in the fin-slot region. An approximate 1:10th scale pie-shaped fin-slot motor was designed to simulate the first segment of the fin-slot RSRM and to perform diagnostic measurements for studying the flow and heat transfer behavior on the exposed propellant surface. The simulation motor consisted of a single, inert triangular fin section mounted in a horizontal, 2-D axisymmetric stainless steel chamber with an observation window. Opposite to this flow-visualization window was an array of 36 flushmounted heat-flux gauges installed on a diagnostic panel in a perpendicular orientation to detect the local temperature rise rates at representative regions of the fin-slot propellant surface. Clean air was compressed in a storage tank and allowed to pass through a heated blow-down wind tunnel for supplying hot airflow through the igniter section and into the fin-slot region at multiple temperature levels, simulating the hot gas products from the igniter. Data from the direct discharge of a live igniter onto an inert fin-slot propellant sample were also collected for comparison with the hot-air heat transfer experiments. Results were used to develop a correlation between the internal flow-field and heat-transfer within the fin-slot region. The heat-transfer rates evaluated from this correlation matched the measured data trend with in the experimental error.",
author = "Moore, {Jeffrey David} and Wehrman, {Robert B.} and Ferrara, {Peter J.} and Kuo, {Kenneth K.}",
year = "2006",
language = "English (US)",
isbn = "1563478188",
volume = "6",
pages = "4456--4467",
booktitle = "Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference",

}

Moore, JD, Wehrman, RB, Ferrara, PJ & Kuo, KK 2006, Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor. in Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference. vol. 6, pp. 4456-4467, AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference, Sacramento, CA, United States, 7/9/06.

Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor. / Moore, Jeffrey David; Wehrman, Robert B.; Ferrara, Peter J.; Kuo, Kenneth K.

Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference. Vol. 6 2006. p. 4456-4467.

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

TY - GEN

T1 - Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor

AU - Moore, Jeffrey David

AU - Wehrman, Robert B.

AU - Ferrara, Peter J.

AU - Kuo, Kenneth K.

PY - 2006

Y1 - 2006

N2 - Fin-slot propellent grains have been used in a variety of solid rocket propulsion systems. Advantages of fin-slot propellant grains include: a constant total burning surface area and thrust level, large burning surface area, large free volume, and greater reliability for ignition. It is known that the fin-slot region has confined space and a complex geometry and the influence of the igniter jet has a profound effect on the flow-field re-circulating patterns, due to its impingement angle, degree of under-expansion, and strength of the induced vortex. In order to accurately predict the overall ignition transient for the reusable solid rocket motors (RSRM) of the Space Shuttle booster with head-end fin slots, it is necessary to have the knowledge of the energy transfer rates in the fin-slot region. An approximate 1:10th scale pie-shaped fin-slot motor was designed to simulate the first segment of the fin-slot RSRM and to perform diagnostic measurements for studying the flow and heat transfer behavior on the exposed propellant surface. The simulation motor consisted of a single, inert triangular fin section mounted in a horizontal, 2-D axisymmetric stainless steel chamber with an observation window. Opposite to this flow-visualization window was an array of 36 flushmounted heat-flux gauges installed on a diagnostic panel in a perpendicular orientation to detect the local temperature rise rates at representative regions of the fin-slot propellant surface. Clean air was compressed in a storage tank and allowed to pass through a heated blow-down wind tunnel for supplying hot airflow through the igniter section and into the fin-slot region at multiple temperature levels, simulating the hot gas products from the igniter. Data from the direct discharge of a live igniter onto an inert fin-slot propellant sample were also collected for comparison with the hot-air heat transfer experiments. Results were used to develop a correlation between the internal flow-field and heat-transfer within the fin-slot region. The heat-transfer rates evaluated from this correlation matched the measured data trend with in the experimental error.

AB - Fin-slot propellent grains have been used in a variety of solid rocket propulsion systems. Advantages of fin-slot propellant grains include: a constant total burning surface area and thrust level, large burning surface area, large free volume, and greater reliability for ignition. It is known that the fin-slot region has confined space and a complex geometry and the influence of the igniter jet has a profound effect on the flow-field re-circulating patterns, due to its impingement angle, degree of under-expansion, and strength of the induced vortex. In order to accurately predict the overall ignition transient for the reusable solid rocket motors (RSRM) of the Space Shuttle booster with head-end fin slots, it is necessary to have the knowledge of the energy transfer rates in the fin-slot region. An approximate 1:10th scale pie-shaped fin-slot motor was designed to simulate the first segment of the fin-slot RSRM and to perform diagnostic measurements for studying the flow and heat transfer behavior on the exposed propellant surface. The simulation motor consisted of a single, inert triangular fin section mounted in a horizontal, 2-D axisymmetric stainless steel chamber with an observation window. Opposite to this flow-visualization window was an array of 36 flushmounted heat-flux gauges installed on a diagnostic panel in a perpendicular orientation to detect the local temperature rise rates at representative regions of the fin-slot propellant surface. Clean air was compressed in a storage tank and allowed to pass through a heated blow-down wind tunnel for supplying hot airflow through the igniter section and into the fin-slot region at multiple temperature levels, simulating the hot gas products from the igniter. Data from the direct discharge of a live igniter onto an inert fin-slot propellant sample were also collected for comparison with the hot-air heat transfer experiments. Results were used to develop a correlation between the internal flow-field and heat-transfer within the fin-slot region. The heat-transfer rates evaluated from this correlation matched the measured data trend with in the experimental error.

UR - http://www.scopus.com/inward/record.url?scp=34249307469&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34249307469&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:34249307469

SN - 1563478188

SN - 9781563478185

VL - 6

SP - 4456

EP - 4467

BT - Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference

ER -

Moore JD, Wehrman RB, Ferrara PJ, Kuo KK. Development of a correlation between internal flow field and heat-flux measurements in a simulated fin-slot rocket motor. In Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference. Vol. 6. 2006. p. 4456-4467