A multidomain and multidimensional numerical analysis of flow in fuelside preburner, high pressure turbine, hot gas manifold and main injector assembly of the Space Shuttle main engine

1987 ◽  
Author(s):  
T. MUKERJEE ◽  
L. TAM ◽  
S. JAIN ◽  
N. COSTES
Keyword(s):  
High Pressure ◽  
Numerical Analysis ◽  
Space Shuttle ◽  
High Pressure Turbine ◽  
Hot Gas ◽  
Main Engine

Numerical analysis of flow in the hot gas manifold of the Space Shuttle main engine

1986 ◽  
Author(s):  
S. OWENS ◽  
T. MUKERJEE ◽  
A. SINGHAL ◽  
A. PRZEKWAS ◽  
D. GLYNN ◽  
...  
Keyword(s):  
Numerical Analysis ◽  
Space Shuttle ◽  
Hot Gas ◽  
Main Engine

scholarly journals Experimental evaluation of an advanced Space Shuttle Main Engine hot-gas manifold design concept

1984 ◽  
Author(s):  
D. PELACCIO ◽  
F. LEPORE ◽  
G. OCONNOR ◽  
G. RAO ◽  
G. RATEKIN ◽  
...  
Keyword(s):  
Experimental Evaluation ◽  
Space Shuttle ◽  
Design Concept ◽  
Hot Gas ◽  
Main Engine

Aerodynamic evaluation of the redesigned Space Shuttle Main Engine hot-gas manifold

1985 ◽  
Author(s):  
S. VOGT ◽  
W. CUAN ◽  
F. HOEHN ◽  
B. KIM ◽  
G. OCONNOR ◽  
...  
Keyword(s):  
Space Shuttle ◽  
Hot Gas ◽  
Main Engine

Cold Flow Testing of the Space Shuttle Main Engine Alternate Turbopump Development High Pressure Fuel Turbine Model

1992 ◽  
Author(s):  
Stephen W. Gaddis ◽  
Susan T. Hudson ◽  
P. Dean Johnson
Keyword(s):  
High Pressure ◽  
Space Shuttle ◽  
Rocket Engine ◽  
Performance Model ◽  
Test Article ◽  
Turbine Performance ◽  
Reynolds Number Effects ◽  
Liquid Rocket ◽  
Turbine Design ◽  
Main Engine

The National Aeronautics and Space Administration’s (NASA’s) Marshall Space Flight Center (MSFC) has established a “cold” airflow turbine test program to experimentally determine the performance of liquid rocket engine turbopump drive turbines. Testing of the space shuttle main engine (SSME) alternate turbopump development (ATD) fuel turbine was conducted for “back-to-back” comparisons with the baseline SSME fuel turbine results obtained in the first quarter of 1991. Turbine performance, Reynolds number effects, and turbine diagnostics, such as stage reactions and exit swirl angles, were investigated at the turbine design point and at off-design conditions. The test data showed that the ATD fuel turbine test article was approximately 1.4 percent higher in efficiency and flowed 5.3 percent more than the baseline fuel turbine test article. This paper describes the method and results used to validate the ATD fuel turbine aerodynamic design. The results are being used to determine the ATD high pressure fuel turbopump (HPFTP) turbine performance over its operating range, anchor the SSME ATD steady-state performance model, and validate various prediction and design analyses.

scholarly journals Numerical Analyses of a Rocket Engine Turbine and Comparison With Air Test Data

1992 ◽  
Author(s):  
Ken Tran ◽  
Daniel C. Chan ◽  
Susan T. Hudson ◽  
Stephen W. Gaddis
Keyword(s):  
High Pressure ◽  
Test Data ◽  
Space Flight ◽  
Space Shuttle ◽  
Rocket Engine ◽  
Second Stage ◽  
Overall Performance ◽  
Main Engine ◽  
Level Of Analysis ◽  
Nasa Marshall Space

Cold air test data on the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine were recently collected at NASA Marshall Space Flight Center (MSFC). The turbine is a two-stage reaction machine, which was designed in the early 1970s (Fig. 1a). Overall performance data, static pressures on the first- and second-stage nozzles, and static pressures along the gas path at the hub and tip were gathered and are compared in this paper with various (1-D, quasi 3-D, and 3-D viscous) analysis procedures. The results of each level of analysis is compared to test data to demonstrate the range of applicability for each step in the design process of a turbine.

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