Friction Factors and Heat Transfer Coefficients for Hydrogen Systems Operating at Supercritical Pressures

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Dunn

Coats

2004

A new model for the design and analysis of a regeneratively cooled rocket engine is developed. In this model two proven rocket thermal analysis codes, TDK and RTE, were conjugated. The integration of these codes was accomplished via an interface file. The accuracy of this combined TDK-RTE model was examined by comparing its results to those of other methods for the SSME and experimental data for a liquid oxygen cooled RP1/LOX engine. Several of the additions and modifications incorporated into this model make it an excellent tool for designing the cooling circuits of regeneratively cooled engines.

Section: Run Tdkmentioning

confidence: 81%

mentioning

confidence: 99%

A Model for Design and Analysis of Regeneratively Cooled Rocket Engines

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Dunn

Coats

2004

“…One side is the temperature of wall exposed to combustion gases (T w ) and the other side is the coolant temperature (T c ). The overall thermal resistance between the wall and coolant is expressed by: [4] and Hendrick [9] correlations can be used. Diprey and Sabersky's correlation, used in this work, is given by:…”

Section: Figure 2: Schematics Of An Engine Broken Into a Number Of Stmentioning

confidence: 99%

“…When the coolant is liquid oxygen the correlation given Spenser and Rousar [10] can be used. To account for the curvature and entrance effects correction factors for Nusselt number given in [9] are used.…”

Section: Figure 2: Schematics Of An Engine Broken Into a Number Of Stmentioning

confidence: 99%

A Simple Approach for Thermal Analysis of Regenerative Cooling of Rocket Engines

Volume 10: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A, B, and C

Foulon

2008

A simple model for thermal analysis of regenerative cooled rocket engines is developed. In this model the multi-dimensional heat conduction in the engine wall is analyzed using the fin effect of cooling channel side walls. A one-dimensional model for the cooling channel flow and heat transfer is used. The coolant properties are evaluated based on the NIST database. The present model is used to perform thermal analysis on two engines: the Space Shuttle Main Engine (a liquid hydrogen cooled engine) and a liquid oxygen cooled engine. Given the simplicity of the present approach its results compare well with other comprehensive models.

“…The coolant flow is formulated based on a onedimensional model, which incorporates supercritical coolant properties, pressure drop, expansion and contraction of cooling channels and curvature effects; The coolant heat fluxes are evaluated based on correlations specifically developed for each coolant. For example, for supercritical liquid hydrogen the correlation suggested by Hendricks et al (1985), and for liquid oxygen the correlation developed by Spencer and Rouser (1977), are used. A complete description of the numerical model for this Rocket Thermal Evaluation model is posted at www.manhattan.edu/~mnaraghi/rte/rte.html.…”

Section: Nodal Points In Radial Directionmentioning

confidence: 99%

Effects of Gas Radiation on the Thermal Characteristics of Regeneratively Cooled Rocket Engines

Heat Transfer, Volume 3

Nunes

2002

This paper studies the effects of radiative heat transfer on the thermal characteristics of regeneratively cooled rocket engines. A conjugated radiative, conductive and convective model is used to analyze the effects of radiative heat transfer in two regeneratively cooled rocket engines. One engine has liquid hydrogen and liquid oxygen as the propellant and liquid hydrogen as the coolant. The other engine has RP1 (a hydrocarbon fuel) and liquid oxygen as the propellant and liquid oxygen as the coolant. It is shown that gas radiation has some effect on the wall temperature of the LH2-LO2 engine and a small effect on its coolant flow characteristics. For the RP1-LO2 engine, however, gas radiation significantly increases the coolant pressure drop, temperature and Mach number. It is also shown that radiation effects must be addressed in cooling channel design, so that wall temperatures and cryogenic coolant flow temperature/pressure are at suitable levels.