SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS

A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 7 - April 7, 2006

07 AIRCRAFT PROPULSION AND POWER
Includes primary propulsion systems and related systems and components, e.g., gas turbine engines, compressors, and fuel systems; and onboard auxiliary power plants for aircraft.

For related information see also 20 Spacecraft Propulsion and Power; 28 Propellants and Fuels; and 44 Energy Production and Conversion.

20060009942 Rolls Royce Corp., Indianapolis, IN, USA

NPSS Multidisciplinary Integration and Analysis

Hall, Edward J.; Rasche, Joseph; Simons, Todd A.; Hoyniak, Daniel; March 2006; 187 pp.; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NAS3-98003; WBS 22-302-15-20; WBS 22-714-09-12 Report No.(s): NASA/CR-2006-213890; E-15261; No Copyright; Avail.: CASI: A09, Hardcopy

The objective of this task was to enhance the capability of the Numerical Propulsion System Simulation (NPSS) by expanding its reach into the high-fidelity multidisciplinary analysis area. This task investigated numerical techniques to convert between cold static to hot running geometry of compressor blades. Numerical calculations of blade deformations were iteratively done with high fidelity flow simulations together with high fidelity structural analysis of the compressor blade. The flow simulations were performed with the Advanced Ducted Propfan Analysis (ADPAC) code, while structural analyses were performed with the ANSYS code. High fidelity analyses were used to evaluate the effects on performance of: variations in tip clearance, uncertainty in manufacturing tolerance, variable inlet guide vane scheduling, and the effects of rotational speed on the hot running geometry of the compressor blades. Author

Turbomachinery; Computational Fluid Dynamics; Structural Analysis; Prop-Fan Technology; Compressor Blades; Guide Vanes; Iteration

20060009979 Siemens Westinghouse Power Corp., Orlando, FL, USA

On-Line Thermal Barrier Coating Monitoring for Real-Time Failure Protection and Life Maximization. (Semi-Annual Report, October 2004-March 2005)

LeMieux, D. H.; Apr. 2005; 26 pp.; In English Report No.(s): DE2005-860801; No Copyright; Avail.: National Technical Information Service (NTIS)

Under the sponsorship of the U. S. Department of Energy's National Energy Laboratory, Siemens Westinghouse Power Corporation proposes a four year program titled, 'On-Line Thermal Barrier Coating (TBC) Monitor for Real-Time Failure Protection and Life Maximization,' to develop, build and install the first generation of an on-line TBC monitoring system for use on land-based advanced gas turbines (AGT). Federal deregulation in electric power generation has accelerated power plant owner's demand for improved reliability availability maintainability (RAM) of the land-based advanced gas turbines. As a result, firing temperatures have been increased substantially in the advanced turbine engines, and the TBCs have been developed for maximum protection and life of all critical engine components operating at these higher temperatures. Losing TBC protection can therefore accelerate the degradation of substrate components materials and eventually lead to a premature failure of critical component and costly unscheduled power outages. This program seeks to substantially improve the operating life of high cost gas turbine components using TBC; thereby, lowering the cost of maintenance leading to lower cost of electricity. Siemens Westinghouse Power Corporation has teamed with Indigo Systems, a supplier of state-of-the-art infrared camera systems, and Wayne State University, a leading research organization in the field of infrared non-destructive examination (NDE), to complete the program. NTIS

Failure; Gas Turbines; On-Line Systems; Protection; Real Time Operation; Thermal Control Coatings

Source: NASA