Design and Experimental Evaluation of a High-Temperature Radial Turbine

Abstract

The findings in this report are not to be construed as an official Department of the Army position unless so designated by other authorized documents. When Government drawings, specifications, or other data are used for any purpose other than in connection with a definitely related Government procurement operation, the U. S. Government thereby incurs no responsibility nor any obligation waatsoever; and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data is not to be regarded by implication or otherwise as in any manner licensing the holder or any other person or corporation, or conveying any rights or permission, to manufacture, use, or sell any patented invention that may in any way be related thereto. DISPOSITION INSTRUCTIONS Destroy this report when no longer needed, inator. Do not return it to the origtamm m " tftn mnustmd DM uffwetmo uiuxaweci D m'.nmm w i iwiiirion/iMiuM'n CVKJ £-Unclassified b<pcunii^l»«»«fic«tio«

Cooling Considerations for Design of a Radial Inflow Turbine

“…The linearization, as explained in Reference 7, can be used to express an equivalent convective heat transfer coefficient due to radiation. This can then be substituted in an expression similar to equation (4) to obtain the following expression for the thermal conductance due to radiation:…”

“…where m is the coolant mass flow rate through the fluid element, C is the specific heat of the coolant, T f is the fluid element temperature, T f-1 and Tf+l are the temperatures of the adjacent fluid elements upstream and downstream respectively, while T j are the temperatures of the J neighboring solid elements. In the foregoing equation the thermal conductance, C fj , can be determined using equation (4).…”

Design Study of an Advanced Concept Simple Gas Turbine for Possible Use in Low Emission Automobiles

“…These tests were run on 10.8-in.-dia wheels, but at reduced pressures and temperatures so that the test Reynolds numbers were 1.86 times that for the SSS 12 engine. The design and analysis received further confirmation as design point efficiencies were met or exceeded on a cooled radial turbine program conducted for the U.S. Army (7,8). Aerodynamic loading on these turbines is kept to modest levels by using a relatively high outlet absolute Mach number, as can be seen by the large difference between total-to-total and total-to-static efficiencies.…”

“…The potential for low NO x emissions of the simple-cycle gas turbine as compared to regenerative/recuperative gas turbines is discussed. These advanced simple-cycle gas turbines are based on an extrapolation of UACLIs perhaps unique radial compressor and turbine design capability (4)(5)(6)(7)(8). This capability has resulted from a continuous program of research and engine application starting in 1961.…”

High-Temperature Radial Turbine Demonstration.

“…h -(1.14 k/D) (pVD/j) 0 5 NPR 0.4 Btu/hr/ft 2 The internal blade smooth passage heat transfer coefficients are calculated, using the empirical expression for turbulent internal flow from duct theory, using local flow areas and hydraulic diameters:…”