SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 19 - SEPTEMBER 23, 2005
07 AIRCRAFT PROPULSION AND POWER - PART I
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.
20050210215 Siemens Westinghouse Power Corp., Orlando, FL, USA
Advanced Turbine Systems Program, Phase III, Technical Progress Final Report
Apr. 2004; 266 pp.; In English Report No.(s): DE2005-828617; No Copyright; Avail: Department of Energy Information Bridge
Natural gas combustion turbines are rapidly becoming the primary technology of choice for generating electricity.At least half of the new generating capacity added in the US over the next twenty years will be combustion turbine systems. The Department of Energy has cosponsored with SiemensWestinghouse, a program to maintain the technology lead in gas turbine systems. The very ambitious eight year program was designed to demonstrate a highly efficient and commercially acceptable power plant, with the ability to fire a wide range of fuels. The main goal of the Advanced Turbine Systems (ATS) Program was to develop ultra-high efficiency, environmentally superior and cost effective competitive gas turbine systems for base load application in utility, independent power producer and industrial markets. Performance targets were focused on natural gas as a fuel and included: System efficiency that exceeds 60% (lower heating value basis); Less than 10 ppmv NO(sub x) emissions without the use of post combustion controls; Busbar electricity that areless than 10% of state of the art systems; Reliability-Availability- Maintainability (RAM) equivalent to current systems; Water consumption minimized to levels consistent with cost and efficiency goals; and Commercial systems by the year 2000. NTIS
Gas Turbines; Turbines
20050212106 NASA Glenn Research Center, Cleveland, OH, USA
High Temperature MEMS for Turbine Engine Applications
Hunter, Gary W.; [2002]; 1 pp.; In English; Spring 2002 Meeting of RTO/AVT MEMS Task Group, 22-26 Apr. 2002, Paris, France; No Copyright; Avail: Other Sources; Abstract Only
The presentation will discuss Microelectromechanical Systems (MEMS) research and development activities and technologies being conducted at NASA Glenn Research Center to address the needs of harsh environment applications. The focus will be on silicon carbide based h4EMS for high temperature, high power and high radiation environment as well as high temperature sensor technologies which are made possible by MEMS processing techniques. These technologies can enable new measurements and capabilities for future turbine engines. All the presentation materials are publicly available and have been presented/published before. Author
Turbine Engines; Microelectromechanical Systems; High Temperature; Systems Engineering; Temperature Sensors; Research and Development
20050212281 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
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Evaluation Techniques for Determining Damping Mechanisms on Titanium Plates
Allen, Kyle S.; Mar. 2005; 145 pp.; In English; Original contains color illustrations Report No.(s): AD-A436467; AFIT/GAE/ENY/05-M01; No Copyright; Avail: CASI; A07, Hardcopy
High cycle fatigue (HCF) is the single largest cause of component failure for all modern military gas turbine engines. Hard coatings, such as magnesium aluminate spinel, have been found to provide significant damping properties. Past studies have had difficulties isolating the contributions of these hard coating damping layers from other damping mechanisms. This study explored techniques for assessing the contribution of different damping mechanisms on titanium plates during vibration testing. The study investigated 2nd bend and 2-stripe modes. Two different specimen sizes were tested in both a clamped-free-free-free and free-free-free-free condition. Specimens were tested at varying pressures. Increases in pressure caused linear peak modal frequency downshifts for both modes of interest for both specimen sizes, and for both boundary conditions. Increases in damping were also seen with increases in pressure for bare plates for the two-stripe mode for both boundary conditions. The clamped boundary condition contributions on the system damping were also investigated. Increases in the stiffness of the cantilevered clamp in the clamped-free-free-free condition were shown to have limited affect on plate damping. DTIC
Damping; Gas Turbines; Metal Plates; Titanium
20050214031 NASA Glenn Research Center, Cleveland, OH, USA
NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts
Manthey, Lri; [2001]; 58 pp.; In English; UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts, 5-6 Sep. 2001, Cleveland, OH, USA; See also 20050214032 - 20050214083; Original contains color and black and white illustrations Contract(s)/Grant(s): RTOP 714-01-4A; No Copyright; Avail: CASI; A04, Hardcopy
Topics discussed include: UEET Overview; Technology Benefits; Emissions Overview; P&W Low Emissions Combustor Development; GE Low Emissions Combustor Development; Rolls-Royce Low Emissions Combustor Development; Honeywell Low Emissions Combustor Development; NASA Multipoint LDI Development; Stanford Activities In Concepts for Advanced Gas Turbine Combustors; Large Eddy Simulation (LES) of Gas Turbine Combustion; NASA National Combustion Code Simulations; Materials Overview; Thermal Barrier Coatings for Airfoil Applications; Disk Alloy Development; Turbine Blade Alloy; Ceramic Matrix Composite (CMC) Materials Development; Ceramic Matrix Composite (CMC) Materials Characterization; Environmental Barrier Coatings (EBC) for Ceramic Matrix Composite (CMC) Materials; Ceramic Matrix Composite Vane Rig Testing and Design; Ultra-High Temperature Ceramic (UHTC) Development; Lightweight Structures; NPARC Alliance; Technology Transfer and Commercialization; and Turbomachinery Overview; etc. Derived from text
Airfoils; Ceramic Matrix Composites; Combustion Chambers; Protective Coatings; Turbomachinery; Thermal Control Coatings; Gas Turbines; Turbine Blades
20050214033 NASA Glenn Research Center, Cleveland, OH, USA
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ASA Multipoint LDI Development
Tacina, Robert; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 8; In English; See also 20050214031; No Copyright; Abstract Only;Available from CASI only as part of the entire parent document
Multipoint Lean-Direct-Injection (LDI) is a combustor concept in which a large number of fuel injectors and fuel-air mixers are used to quickly and uniformly mix the fuel and air so that ultralow levels of NO, are produced. Each fuel injector has an air swirler associated with it for fuel-air mixing and to establish a small recirculation and burning zone. A concept in which there are 36 fuel injectors in the space of a conventional single fuel injector has been tested in a flame tube. A greater than 80 percent reduction in NO, at high power conditions (400 psia, 1000 ‘Finlet) was achieved. Alternate concepts with 9,25,36 or 49 fuel injectors are being investigated in flame tube tests for their low NO, potential and with fuel staging to improve the turn-down ratio at low power conditions. A preliminary sector concept of a large engine design has been successfully tested at inlet conditions of 700 psia and 1100 O F . This concept had one half the number of fuel injectors per square inch as the flame tube configuration with 36 fuel injectors, and the NO, reduction was 65 percent of the ICAO standard. Future regional engine size sector tests are planned for the 2nd quarter of FY02 and large engine size sector tests for the 1st quarter of FY03. Author
Combustion Chambers; Combustion; Engine Design; Fuel Injection
20050214035 NASA Glenn Research Center, Cleveland, OH, USA
Compressor Flow Control Concepts, 2, UEET Compressor Flow Control Modeling
Chima, Rodrick V.; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 28; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
Several passive flow control devices have been modeled computationally in the Swift CFD code. The models were applied to the first stage rotor and stator of the baseline UEET compressor in an attempt to improve efficiency and/or stall margin. The devices included suction surface bleed, tip injection, self-aspirated rotors, area-ruled casing, and vortex generators. The models and computed results will be described in the presentation. None of the results have shown significant gains in efficiency; however, casing vortex generators have shown potential improvements in stall margin. Author
Computational Fluid Dynamics; Control Equipment; Flow Distribution; Vortex Generators; Injection; Suction; Compressors
20050214036 General Electric Aircraft Engines, Cincinnati, OH, USA
Aspiration in Highly Loaded Axial Compressor Design
Tseng, Tom; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 46; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
NASA’s objectives for the Ultra-Efficient Engine Technology (UEET) program include the demonstration of compression systems with increased work per stage and higher efficiency relative to current practice. One concept being proposed to achieve this objective is to aspirate the high loss, viscous layers from the compressor blading. Recent work under a DARPA sponsored program to design a very highly loaded fan stage using the aspiration concept coupled with a unique inverse design technique has indicated that significantly increased loading levels can be obtained at good efficiency levels. The present effort will apply this same aspiration concept to design axial compressor blading capable of delivering a 12:l pressure ratio in four axial stages at 1250 ft/sec design tip speed. Author
Turbocompressors; Compressor Blades; Pressure Ratio; Tip Speed
20050214040 Honeywell Engines, Systems and Services, Phoenix, AZ, USA
Honeywell Low Emissions Combustor Development
Kuhn, Terrel; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 7; In English; See also 20050214031; No Copyright; Abstract Only;Available from CASI only as part of the entire parent document
Honeywell Engines & Systems is currently developing combustor technologies for regional air transport turbofan engines that will enable 70 percent reductions in NO, emissions. The lowest risk concept is lean- direct fuel injection (LDI), wherein the main fuel is partially premixed before entering the main combustion chamber. The LDI design is being optimized using laser diagnostic techniques in preparation for flame-tube and sector rig tests at NASA Glenn and full annular rig tests at Honeywell. Honeywell is working actively with a multipoint LDI fuel injection technology being developed by NASA Glenn to assure applicability of the technology to a regional turbofan application. A third concept that integrates the diffuser and the combustor will be studied. Author
Combustion Chambers; Fuel Injection; Fabrication
20050214044 Army Research Lab., Cleveland, OH, USA
Turbomachinery Overview
Civinskas, Kestutis; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 24; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
One of the UEET program goals is to provide propulsion technologies to enable a 15 percent reduction in C02 emissions (relative to the best-in-service systems in 1999) for large subsonic transports and 8 percent for supersonic and/or small aircraft. The Highly-Loaded Turbomachinery Project is providing the enhanced turbomachinery capability and efficiency to enable the higher overall cycle pressure ratios and turbine inlet temperatures required to meet these overall fuel burn and CO2 reduction goals. The technologies are relevant to a wide range of flight speed and size-class applications. While some work builds upon earlier efforts (AST, HSR, Propulsion Base), this project is largely a new start to explore and develop some radical turbomachinery capability with low starting TRL. This project focuses on fan, compressor, and turbine technologies for reduced-stage, efficient but lightweight cores, low-pressure (LP) spools, and propulsors for highly efficient and environmentally compatible propulsion systems. Concepts for significantly increased aerodynamic loading of turbomachinery, trailing edge wake control, and incorporation of highly effective cooling will be developed and demonstrated. Fan technology development will be collaboratively worked with the QAT Program to maintain efficiency while satisfying reduced noise goals. Flow control techniques are being explored for fan, compressor and turbine components and selected concepts will be demonstrated through proof-of-concept tests. Physics-based models for flow control and cooling will be developed and validated. Advanced CFD codes with physics- based models incorporated will be applied to select promising concepts and to design component hardware for rig test demonstrations of fan, core compressor, and HP/LP turbine systems to reach TRL 34. Author
Turbomachinery; Carbon Dioxide; Inlet Temperature; Turbines; Pressure Ratio; Propulsion System Performance; Propulsion System Configurations; Control Systems Design; Computational Fluid Dynamics
20050214046 NASA Glenn Research Center, Cleveland, OH, USA
Highly Loaded Low Pressure Turbine (LPT)
Ortiz, Milt; Dalsania, Vithal; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 31; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
The goal of this study is to evaluate aspirated and non-aspirated aerodynamics on highly loaded LPT design. The objective is to increase stage loading by 30 to 50 percent without loss of efficiency for an existing low pressure turbine design. A study conducted on a NASA highly loaded multistage fan drive turbine (NASA CR-1964) indicated that end-wall bleed at the hub is a more significant parameter compared to aspirated airfoil. Based on this study, a 3-stage LPT is redesigned to 2-stage LIT with and without end-wall bleed. Both aerodynamic design and mechanical design are completed. In addition to end-wall bleed, exit guide vanes are designed with aspirated airfoils to reduce the losses. The LPT is redesigned with all constraints necessary for practical application. The benefit of the high-performance, highly loaded LPT shows up in reduced stage and part count, reduced size and weight, and reduced cost. Author
Low Pressure; Turbines; Aerodynamics; Airfoils; Guide Vanes; Mechanical Engineering
20050214048 NASA Langley Research Center, Hampton, VA, USA
Propulsion Airframe Integration Overview NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts
[2001], pp. 34; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
The Propulsion Airframe Integration (PAI) Project develops advanced technologies to yield lower drag integration of the propulsion system with the airframe. Lower drag reduces aircraft fuel burn for a given mission, and therefore contributes to the UEET Program s 15 percent CO2 emission reduction goal for large commercial jet transports. An overview of the PAI technologies and plans is given in this presentation. Author
Airframes; Propulsion System Configurations; Engine Airframe Integration; Systems Integration; Carbon Dioxide
Source: NASA.
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