Impact of ETO propellants on the aerothermodynamic analyses of propulsion components

Abstract

The operating conditions and the propellant transport properties used in Earth-to-Orbit (ETO) applications affect the aerothermodynamic design of ET0 turbomachinery in a number of ways. This paper discusses some aerodynamic and heat transfer implications of the low molecular weight fluids and high Reynolds number operating conditions on future ET0 turbomachinery. Using the current SSME high-pressure fuel turbine as a baseline, the aerothermodynamic comparisons are made for two alternate fuel turbine geometries. The first is a revised first-stage rotor blade designed to reduce peak heat transfer. This alternate design resulted in a 23% reduction in peak heat transfer. The second design concept was a single-stage rotor to yield the same power output as the baseline twostage rotor. Since the rotor tip speed was held constant, the turbine work factor doubled. In this alternate design the peak heat transfer remained the same as the baseline. While the efficiency of the single-stage design was 3.1 points less than the baseline two-stage turbine, the design was aerothermodynamically feasible, and may be structurally desirable.

Prediction of the Aerodynamic Environment and Heat Transfer for Rotor-Stator Configurations

“…Figures 12 and 13 show Stanton number profiles for the SSME HPFTP first stator and first rotor. The STAN5 results shown correspond to a calculation which incorporated real gas properties associated with a 0.9813 0/F ratio in the upstream preburner and are consistent with results presented by Civinskas, et al (1988) for the same rotor. A discrepancy between the ROTOR1 and STAN5 predictions is apparent.…”

“…Improvements in these codes include the capability to utilize actual mixture properties of gaseous H2 and steam and the capability in MTSBL to automatically generate an input stream for use with STAN5 for more accurate heat transfer prediction than is available from BLAYER. The heat transfer profile in the leading edge region was approximated using the experimental correlation shown by Civinskas, et al (1988). The quasi-3D procedure of MTSBL assumes a single blade row.…”

“…Predictive capability is assessed in terms of accuracy of calculated airfoil aerodynamic and thermal loads and in terms of suitability for rocket propulsion applications. Relevant rocket propulsion issues are discussed by Civinskas, et al (1988). Although only one unsteady code was used, it is believed that the qualitative results obtained and issues raised are relevant to most unsteady turbine stage codes.…”