The progress report for the grant entitled 'Hypervelocity of Scramjet Combustor-Nozzle Analysis and Design' is presented. The three main tasks in the program are combustor modeling study, development of anaylsis capabilities for hypersonic scramjet nozzles, and development of optimum design methods for hypersonic scramjet nozzles. The research performed was documented in a series of technical publications and presentations at various conferences. A brief description of the research in each of the above three areas and a list of the resulting technical publications are included

Hoffman, Joe D.

Thompson, H. Doyle

English

NASA Technical Reports Server

• ° NASA-CR-190965
HYPERVELOCITY SCRAM JET COMBUSTOR-NOZZLE
ANALYSIS AND DESIGN
Final Report
/o7  /oo
p.
for
NASA Grant NAG-I-854
for the period
15 February 1988 to 31 December lggl
Prepared by
H. Doyle Thompson and Joe D. Hoffman, Principal Investigators
Thermal Sciences and Propulsion Center
School of Mechanical Engineering
Purdue University
West Lafayette, IN 47907
Submitted to
NASA Langley Research Center
ATTN: John P. Weidner
Technical Director, MS 168
Hampton, VA 23665
November 1992
(NASA-CR-190965) HYPERVELOCITY
SCRAMJET COMBUSTOR-NOZZLE ANALYSIS
AND DESIGN Final Technical Report,
15 Feb. Iq88 - 31 Dec. 19qi
(Purdue Univ.) 6 p
N93-12214
Unclas
GB/07 0127100
\
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https://ntrs.nasa.gov/search.jsp?R=19930003026 2020-03-17T10:28:32+00:00Z
PRECEDING PAGE BLANK NOT FILME'O
I. INTRODUCTION
This is the Final Technical Report for NASA Grant NAG-I-854 entitled
'_ypervelocity Scramjet Combustor-Nozzle Analysis and Design." The first phase
of the Grant was for the period 15 February 1988 through December 1988, with a
no cost extension through 28 February 1989. The second phase was for the
period 1 March 1989 through 28 February 1990. The third phase was for the
period 1 March 1990 through 28 February 1991, with a no cost extension through
31 December 1991. The research was performed at Purdue University, West
Lafayette, IN, under the direction of Professors H. Doyle Thompson and Joe D.
Hoffman, both of the School of Mechanical Engineering. The technical monitor is
Mr. John Weidner of NASA Langley Research Center.
There are three tasks associated with this Grant. The first has been renamed
in keeping with the redirected emphasis from a Vitiated Air Study to a
Combustor Modeling Study. The three main tasks in the program are:
I. Combustor Modeling Study
II. Development of Analysis Capabilities for Hypersonic Scramjet Nozzles
HI. Development of Optimum Design Methods for Hypersonic Scramjet Nozzles
The research performed under NASA Grant NAG 1-854 has been documented
in a series of technical publications and presentations at various conferences. A
brief description of the research in each of the above three areas and a list of the
resulting technical publications constitutes this final report.
3H. COMBUSTOR MODELING
DES CRIPTION
The objective of this task was to develop an analysis capability and a
computer code for modeling the processes occurring in a scramjet combustor.
The computer code that was developed is called 3STREAM.
3STREAM utilizes the one dimensional chemical kinetics code GKSP87
developed by D. Bittker and V. Scullin* at NASA Lewis Research Center. A
procedure for incorporating the effects of mixing, heat transfer, and friction into
the GKSP87 kinetics code was developed. The procedure involves a three-stream
flow model composed of oxidizer, fuel, and products streams; an ignition source; a
mixing schedule; interstream and environmental heat transfer; wall friction for
the oxidizer and fuel streams; and turbulent mixing losses in the products stream.
The code was developed and tested, and is currently being used by several
government laboratories and contractors to parametrically evaluate the effect of
various parameters on supersonic combustion, and for modeling a variety of
supersonic combustion processes.
PUBLICATIONS
1. Houck, S.W., "3STREAM: An Engineering Tool for Modeling Complex
Combustion Processes," MSE Thesis, Purdue University, W. Lafayette, IN,
December 1989.
2. Houck, S.W., Hoffman, J.D., and Thompson, H.D., "3STREAM: A Simple
Engineering Tool for Modeling Supersonic Combustion," Paper Number 58,
Seventh National Aero-Space Plane Technology Sympossum, NASA Lewis
Research Center, October 23-27, 1989.
3. Houck, S.W., Hoffman, J.D., and Thompson H.D., "3STREAM: An
Engineering Tool for Modeling Complex Combustion Processes: Volume 1:
Theory, Development and Results," NASP Contractor Report 1093, August
1990.
4. Houck, S.W., Hoffman, J.D., and Thompson, H.D., "3STREAM: An
Engineering Tool for Modeling Complex Combustion Processes: Volume 2:
Program Users Guide," NASP Contractor Report 1094, August 1990.
5. Trexler, C.A., Weidner, J.P., and Thompson, H.D., "Summary of
Hypersonic Inlet TMP-101 and Nozzle TMP-103, 10th National Aero-Space
Plane Symposium, Monterey, CA, Paper Number 111, April 23-26, 1991.
6. Houck, S.W., Hoffman, J.D., and Thompson, H.D., "3STREAM: An
Engineering Tool for Modeling Complex Combustion Processes," paper in
preparation for the AiAA Journal of Propulsion and Power.
* Bittker, David A., and Scullin, Vincent J., "GCKP84 - General Chemical Kinetics Code for GaJ-Phase Flow and Batch
Proc_,ses Including Heat Transfer Effects," NASA Technical Paper 232D, September 1084.
III. ANALYSIS CAPABILITY
DESCRIPTION
The objective of this task was to develop the analysis and the computer codes
that are capable of analyzing steady flow through scramjet nozzles. The nozzle
geometries to be analyzed include both test geometries and flight geometries. The
codes have the capability of handling arbitrary free stream conditions, so that the
effects of different flight conditions can be considered. They require the
specification of the exit conditions from the combustor, although these conditions
may be specified as any realistic set of values.
The original intent was to develop both two-dimensional and three-
dimensional analysis codes. However, the three-dimens|onal code has not been
successfully developed.
A two-dimensional code has been developed and has been used as part of the
optimum nozzle design study in both the hinged flap design study and the direct
optimization maximum thrust nozzle design procedure.
The details of the two-dimensional computer code and its use are contained in
the following publications.
PUBLICATIONS
7. Dory, J.H., 'Performance Prediction and Design of Maximum Thrust Planar
Supersonic Nozzles Using a Flux-Difference-Splltting Technique," Ph.D.
Thesis, Purdue University, W. Lafayette, IN, August 1991.
8. Doty, J.H., Thompson, H.D., and Hoffman, J.D., '_Performance Prediction
and Design of Maximum Thrust Planar Supersonic Nozzles Using a Flux-
Difference-Splitting Technique; Volume 1: Theory, Development and
Results," Technical Report submitted to NASA-Langley (Mr. John Weidner)
for approval, publication, and distribution,August, 1991.
9. Doty, J.H. Thompson, H.D., and Hoffman, J.D., "Performance Prediction
and Design of Maximum Thrust Planar Supersonic Nozzles Using a Flux-
Difference-SplittingTechnique; Volume 2: Program Users Guide," Technical
Report in progress.
1%r. OPTIMUM NOZZLE DESIGN CAPABILITY
DESCRIPTION
The objective of this task is to develop the criteria, and the associated
computer codes, to implement optimum design procedures for seramjet type
nozzles. Optimum design implies the determination of the variables that are at
the designer's discretion, subject to the fixed constraints of the problem, that will
produce the maximum net nozzle thrust. Several optimization problems have
been identified that have direct application to the seramjet nozzle problem. They
include:
1. Determination of the optimum supersonic nozzle contour for maximum
thrust, subject to constraints on geometric parameters such as overall
length, etc.,
2. Determination of the optimum flap angle for a fixed geometry nozzle
operating at off-deslgn conditions,
3. Determination of the opt|mum nozzle contour as in 1 above, but subject to
a trim drag penalty, and
4. Determination of the effect of non-unlform inlet conditions on the optimum
contours.
The publications listed below include the results of all of the applicable
optimization problems, including the analysis, development of the requisite
computer codes, and the computation of optimum designs. It should be noted
that the determination of optimum geometries requires the use of an accurate
analysis computer code. Thus the analysis capability is an important part of the
optimum nozzle design capability.
As a final note a comparison of the optimum two-dimensional contours
determined under this program with those generated by the Rao optimization
techniques* revealed that under certain conditions the Rao technique gives a
minimum (local minimum) thrust instead of a maximum thrust.
PUBLICATIONS
10. Dory, J.H., Thompson, H.D., and Hoffman, 5.D., "Generalized Optimization
of Two-Dimensional Nozzles Including Trim Drag," Proceedings o/the 1989
JANNAF Propulsion Conference, May 1989.
11. Dory, J.H., Thompson, H.D., and Hoffman, J.D., '_Iaximum Thrust Nozzles
With Non-Unlform Inlet Conditions," NASP CR-1069, October 1080.
12. Dory, J.H. Thompson, H.D., and Hoffman, J.D., '_VIaximum Thrust
Airframe-Integrated Seramjet Nozzles," Paper Number 83, Seventh National
Aero-Spaee Plane Technology Symposium, NASA Lewis Research Center,
October 23-27, 1980.
* Rao, G.V.R., "ExlaausL Nozzle Contour for Optimum Tlarusl;," Jet Propul#io._ 28, 1958, pp. 377-382.
13. Dory, J.H., Thompson, H.D., and Hoffman, J.D., "Optimum Thrust
Supersonic Nozzles for Hypersonic Vehicles; Volume 1: Theory and Results,"
Technical report submitted to NASA-Langley (Mr. John Weidner) for
approval, publication and distribution on 24 January 1992.
14. Dory, J.H., Thompson, H.D., and Hoffman, J.D., "Optimum Thrust
Supersonic Nozzles for Hypersonic Vehicles; Volume 2: Program Users
Guide," Technical Report in progress.
15. Dory, J.H., Thompson, H.D., and Hoffman, J.D., "A Rao Thrust Nozzle
Optimization Sometimes is a Minimum," teehn|eal note, in preparation for
the AIAA Journal of Propulsion and Power.


Hypervelocity scramjet combustor-nozzle analysis and design

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