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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 433 records · Page 24
All sourcesNASA NTRSDOE OSTI
DOE OSTI2012

An Undergraduate Minor in Wind Energy at Iowa State University (Final Report)

This report describes an undergraduate minor program in wind energy that has been developed at Iowa State University. The minor program targets engineering and meteorology students and was developed to provide interested students with focused technical expertise in wind energy science and engineering, to increase their employability and ultimate effectiveness in this growing industry. The report describes the requirements of the minor program and courses that fulfill those requirements. Five new courses directly addressing wind energy have been developed. Topical descriptions for these five courses are provided in this report. Six industry experts in various aspects of wind energy science and engineering reviewed the wind energy minor program and provided detailed comments on the program structure, the content of the courses, and the employability in the wind energy industry of students who complete the program. The general consensus is that the program is well structured, the course content is highly relevant, and students who complete it will be highly employable in the wind energy industry. The detailed comments of the reviewers are included in the report.

17 WIND ENERGY↗
NASA NTRS1948

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine: Performance and Windmilling Drag Characteristics - Part 5

An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. Performance of the original and modified engines is compared for a range of simulated flight conditions. The performance data are generalized to show the applicability of methods used to estimate performance at any altitude from data obtained at a given altitude. Engine-windmilling-speed and windmilling-drag data are presented for a range of simulated flight conditions.

Meyer, Carl L.↗
NASA NTRSDate not supplied

NASA's Unsteady Pressure-Sensitive Paint Research and Operational Capability Developments

In the last three years, several advancements have been made to produce a new state-of-the-art capability in the field of Aerosciences. NASA’s Aerosciences Evaluations and Test Capabilities (AETC) Portfolio Office has funded a multi-year project to produce the unsteady Pressure-Sensitive Paint (uPSP) technology as an operational capability in key ground test facilities at NASA. The research and development has primarily been conducted at NASA Ames Research Center’s (ARC) Unitary Plan Wind Tunnel (UPWT) 11-by 11-ft Transonic Wind Tunnel (TWT). The NASA ARC UPWT is one of the ground test facilities under NASA AETC’s Portfolio Office. AETC’s goals are to provide the tools to deliver the technology innovations and breakthroughs necessary to address increasingly complex research and development challenges. AETC’s integrated approach will consider the complimentary high-end compute capabilities necessary to advance analysis in conjunction with ground experimental capabilities. The uPSP Capability Challenge Project is a demonstration of several different technologies: 1) the unsteady Pressure-Sensitive Paint (uPSP) technology, and 2) Project: Red Rover, establishing a secure, reliable, fast connection between experimental and computation facilities, leveraging NASA’s computational resources within the High-End Compute Capability (HECC) Project for processing, storing, and sharing data efficiently. This project demonstrates the technical diversity and technical inclusion need to advance the field of Aerosciences. The approach to combine subject matter experts in experimental methods, optical methods, production wind tunnel testing, network engineering, high-end computing, signal processing, grid generation, and visualization while establishing the required infrastructure for subject matter experts to have access to the data while the wind tunnel test is being conducted. The most recent advancements for the uPSP technology have focused on three key areas: development of data products, robust processing pipeline, operational efficiencies and uncertainty quantification.

buffet↗
DOE OSTI2017

Chapter 15: Reliability of Wind Turbines

The global wind industry has witnessed exciting developments in recent years. The future will be even brighter with further reductions in capital and operation and maintenance costs, which can be accomplished with improved turbine reliability, especially when turbines are installed offshore. One opportunity for the industry to improve wind turbine reliability is through the exploration of reliability engineering life data analysis based on readily available data or maintenance records collected at typical wind plants. If adopted and conducted appropriately, these analyses can quickly save operation and maintenance costs in a potentially impactful manner. This chapter discusses wind turbine reliability by highlighting the methodology of reliability engineering life data analysis. It first briefly discusses fundamentals for wind turbine reliability and the current industry status. Then, the reliability engineering method for life analysis, including data collection, model development, and forecasting, is presented in detail and illustrated through two case studies. The chapter concludes with some remarks on potential opportunities to improve wind turbine reliability. An owner and operator's perspective is taken and mechanical components are used to exemplify the potential benefits of reliability engineering analysis to improve wind turbine reliability and availability.

17 WIND ENERGY↗
NASA NTRS1948

Altitude-wind-tunnel investigation of performance and windmilling drag characteristics of Westinghouse X24C-4B axial-flow turbojet engine

An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. Performance of the original and modified engines is compared for a range of simulated flight conditions. The performance data are generalized to show the applicability of methods used to estimate performance at any altitude from data obtained at a given altitude. Engine-windmilling-speed and windmilling-drag data are presented for a range of simulated flight conditions.

Meyer, Carl L↗
DOE OSTI2017

2016 Offshore Wind Technologies Market Report

The 2016 Offshore Wind Technologies Market Report was developed by the National Renewable Energy Laboratory (NREL) for the U.S. Department of Energy (DOE) and is intended to provide offshore wind policymakers, regulators, developers, researchers, engineers, financiers, and supply chain participants, with quantitative information about the offshore wind market, technology, and cost trends in the United States and worldwide. In particular, this report is intended to provide detailed information on the domestic offshore wind industry to provide context to help navigate technical and market barriers and opportunities. The scope of the report covers the status of the 111 operating offshore wind projects in the global fleet through December 31, 2016, and provides the status and analysis on a broader pipeline of 593 projects at some stage of development. In addition, this report provides a wider assessment of domestic developments and events through the second quarter of 2017 to provide a more up-to-date discussion of this dynamically evolving industry.

17 WIND ENERGY↗
NASA NTRS1982

Wind tunnel tests of a zero length, slotted-lip engine air inlet for a fixed nacelle V/STOL aircraft

Zero length, slotted lip inlet performance and associated fan blade stresses were determined during model tests using a 20 inch diameter fan simulator in the NASA-LeRC 9 by 15 foot low speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. The inlet performance was dependent on slot gap width and relatively independent of inlet throat/fan face spacer length and slot flow blockage created by 90 degree slot fillers. Optimum performance was obtained at a slot gap width of 0.36 inch. The zero length, slotted lip inlet satisfied all critical low speed inlet operating requirements for fixed horizontal nacelles subsonic V/STOL aircraft.

Woollett, R. R.↗
NASA NTRS1973

Technical feasibility study for the development of a large capacity wind powered electrical generating system

The engineering feasibility of developing a basic mechanical system necessary for extracting large amounts of power (on the order of 10 to 20 MW) from the wind is considered using the concept of vertical airfoils moving along a closed horizontal track system. Attention is focused on those components necessary for the conversion of wind energy to mechanical energy, although the general characteristics and critical aspects of other components are also considered. The four phases of this program are: (1) Establishment of component specifications and interface requirements for major system components; (2) formulation of alternative sets of conceptual designs for major system components; (3) engineering analysis of various components and systems; and (4) re-examination of basic concept and identification of any desirable follow-up work.

Powe, R. E.↗
NASA NTRS1948

Altitude-Wind-Tunnel investigation of Westinghouse 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines IV : analysis of compressor performance

Investigations were conducted in the NACA Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-6, and 19XB-1 Turbojet Engines. One objective of the investigations was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively. The data were obtained over a range of simulated altitudes and flight Mach numbers. At each simulated flight condition the engine was run over its full operable range of speeds. Performance characteristics of the 19B-8 and 19XB-1 compressors for the range of operation obtainable in the turbojet-engine installation are presented. Compressor characteristics are presented as functions of air flow corrected to sea-level conditions, compressor Mach number, and compressor load coefficient.

Dietz, Robert O↗
NASA NTRSDate not supplied

Mitigation of Nacelle/Pylon Wake on the High-Lift Common Research Model Using a Nacelle Chine

A 10% scale, high-lift version of the Common Research Model (CRM-HL) was tested in the NASA Langley Research Center 14-by22-Foot Subsonic Tunnel. The focus of the wind tunnel test campaign was to assess the feasibility of active flow control (AFC) on the simplified CRM-HL configuration. The modular design of the CRM-HL model enabled the testing of the conventional CRM-HL version to establish a benchmark for the AFC research. The wind tunnel model has the capability of being tested with and without the engine nacelle/pylon for comparison. The wind tunnel investigation included the acquisition of force and moment data, steady pressure data, as well as surface flow visualization using minitufts. For some select cases, numerical simulations were performed to aid in understanding the wind tunnel data. Wind tunnel measurements indicated a lift degradation of the conventional CRM-HL at high angles of attack. The surface flow visualization with fluorescent minitufts revealed that the lift degradation is due to flow separation caused by the nacelle/pylon wake on the inboard wing. The wake and the consequent flow separation were successfully mitigated using a nacelle chine installed on the inboard side of the engine nacelle.

Mehti Koklu↗
NASA NTRS1948

Altitude-Wind-Tunnel Investigation of Westinghouse 19B-2 19B-8, and 19XB-1 Jet-Propulsion Engines: Operational Characteristics - Part 1

An investigation was conducted in the NACA Cleveland altitude wind tunnel to determine the operational characteristics of the Westinghouse 19B-2, 19B-8, and 19XB-l jet-propulsion engines. The 19B engine is one af the earliest experimental Westinghouse axial flow engines. The 19XB-1 engine is an experimental prototype of the Westinghouse 15 series, having a rated thrust of 1400 pounds. Improvements in performance and operational characteristics have resulted in the 19XB-2B engine with a rated thrust of 1600 pounds. The operational characteristics were determined over a range of simulated altitudes from 5000 to 30,000 feet for the 19B engines and from 5000 to 35000 feet for the 19XB-l engine at airspeed from 20 to 380 miles per hour. The affects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, starting, acceleration, and functioning of the fuel-control system are discussed. Damage to the engines that occurred during the investigation is also briefly discussed. The changes made in the combustion-chamber configuration to improve the operating we are described.

Fleming, William A.↗