High Temperature Aircraft Turbine Engine Bearing and Lubrication System Development

2009 ◽  
pp. 409-409-26 ◽  
Author(s):  
DH Grant ◽  
HA Chin ◽  
C Klenke ◽  
AT Galbato ◽  
MA Ragen ◽  
...  
Keyword(s):  
High Temperature ◽  
System Development ◽  
Lubrication System ◽  
Turbine Engine ◽  
Engine Bearing

TIMETAL 829

Alloy Digest ◽  
2001 ◽  
Vol 50 (8) ◽  
Keyword(s):  
Fracture Toughness ◽  
Titanium Alloy ◽  
High Temperature ◽  
High Strength ◽  
Heat Treating ◽  
High Temperature Alloy ◽  
Turbine Engine ◽  
Major Application ◽  
Alpha Titanium ◽  
Engine Components

Abstract TIMETAL 829 is a Ti-5.5Al-3.5Sn-3Zr-1Nb-0.25Mo-0.3Si near-alpha titanium alloy that is weldable and has high strength and is a creep resistant high temperature alloy. The major application is as gas turbine engine components. This datasheet provides information on composition, physical properties, elasticity, and tensile properties as well as fracture toughness, creep, and fatigue. It also includes information on forming and heat treating. Filing Code: TI-118. Producer or source: Timet.

TIMETAL 551

Alloy Digest ◽  
2006 ◽  
Vol 55 (5) ◽  
Keyword(s):  
Shear Strength ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbine ◽  
Heat Treating ◽  
Nominal Composition ◽  
Turbine Engine ◽  
Temperature Performance ◽  
Beta Alloy ◽  
Alpha Beta

Abstract Timetal 551 is an improved-strength version of Timetal 550 alloy that retains good forging characteristics. The alpha-beta alloy has a nominal composition of Ti-4Al-4Mo-4Sn-0.5 Si, and it is used in gas turbine engine parts. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as creep. It also includes information on high temperature performance as well as forming and heat treating. Filing Code: TI-138. Producer or source: Timet.

Siemens Westinghouse Advanced Turbine Systems Program Final Summary

2002 ◽  
Author(s):  
Ihor S. Diakunchak ◽  
Greg R. Gaul ◽  
Gerry McQuiggan ◽  
Leslie R. Southall
Keyword(s):  
High Temperature ◽  
High Efficiency ◽  
Technology Development ◽  
Mechanical Design ◽  
System Development ◽  
Department Of Energy ◽  
Combustion Heat ◽  
Alloy Casting ◽  
Generation Plant ◽  
Power Generation Plant

This paper summarises achievements in the Siemens Westinghouse Advanced Turbine Systems (ATS) Program. The ATS Program, co-funded by the U.S. Department of Energy, Office of Fossil Energy, was a very successful multi-year (from 1992 to 2001) collaborative effort between government, industry and participating universities. The program goals were to develop technologies necessary for achieving significant gains in natural gas-fired power generation plant efficiency, a reduction in emissions, and a decrease in cost of electricity, while maintaining current state-of-the-art electricity generation systems’ reliability, availability, and maintainability levels. Siemens Westinghouse technology development concentrated on the following areas: aerodynamic design, combustion, heat transfer/cooling design, engine mechanical design, advanced alloys, advanced coating systems, and single crystal (SC) alloy casting development. Success was achieved in designing and full scale verification testing of a high pressure high efficiency compressor, airfoil clocking concept verification on a two stage turbine rig test, high temperature bond coat/TBC system development, and demonstrating feasibility of large SC turbine airfoil castings. The ATS program included successful completion of W501G engine development testing. This engine is the first step in the W501ATS engine introduction and incorporates many ATS technologies, such as closed-loop steam cooling, advanced compressor design, advanced sealing and high temperature materials and coatings.

Modeling of a Unique High-Temperature Turbine Engine Variable Guide Vane Actuator

2008 ◽  
Author(s):  
Matt Caspermeyer ◽  
David Shields ◽  
Harvey Jansen ◽  
Bud Watts ◽  
Russell White
Keyword(s):  
High Temperature ◽  
Guide Vane ◽  
Turbine Engine

Microphone High-Temperature Test System Development Based on PID Control

2014 ◽  
Vol 912-914 ◽  
pp. 1294-1298
Author(s):  
Li Yan Zhao
Keyword(s):  
High Temperature ◽  
System Development ◽  
Test System ◽  
Lower Efficiency ◽  
Temperature Function ◽  
Control Center ◽  
Marketing Application ◽  
High Temperature Operation ◽  
Very High ◽  
Temperature Test

With PID as its control center, this system overcomes the uncontrol of temperature, lower efficiency, difficult operation and other drawbacks occurring in precious microphone high-temperature test system. Characterized by excellent adaptability, automatic heating and constant temperature function, and simple operation, the high-temperature test system can meet the special requirements during microphone high temperature operation, evaluate the phase, frequency response, background noise and other product indexes in a high temperature ambient, and possess a very high marketing application value.

Epoxy-free high-temperature fiber optic pressure sensors for gas turbine engine applications

2004 ◽  
Author(s):  
Juncheng Xu ◽  
Gary Pickrell ◽  
Bing Yu ◽  
Ming Han ◽  
Yizheng Zhu ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fiber Optic ◽  
Pressure Sensors ◽  
Gas Turbine Engine ◽  
Turbine Engine

Leak detection in the lubrication system of an aircraft turbine engine

2011 ◽  
pp. 566-571
Author(s):  
L Rakoto ◽  
M Kinnaert ◽  
M Strengnart ◽  
N Raimarckers
Keyword(s):  
Leak Detection ◽  
Lubrication System ◽  
Turbine Engine

Cyclic Oxidation and Hot Corrosion Behavior of Nickel–Iron-Based Superalloy

2018 ◽  
Vol 37 (2) ◽  
pp. 173-180 ◽  
Author(s):  
D. Chellaganesh ◽  
M. Adam Khan ◽  
J. T. Winowlin Jappes ◽  
S. Sathiyanarayanan
Keyword(s):  
High Temperature ◽  
Corrosion Behavior ◽  
Hot Corrosion ◽  
Prolonged Exposure ◽  
Xrd Analysis ◽  
Mass Change ◽  
Temperature Oxidation ◽  
Turbine Engine ◽  
Nickel Iron ◽  
Iron Based

AbstractThe high temperature oxidation and hot corrosion behavior of nickel–iron-based superalloy are studied at 900 ° and 1000 °C. The significant role of alloying elements with respect to the exposed medium is studied in detail. The mass change per unit area was catastrophic for the samples exposed at 1000 °C and gradual increase in mass change was observed at 900 °C for both the environments. The exposed samples were further investigated with SEM, EDS and XRD analysis to study the metallurgical characteristics. The surface morphology has expressed the in situ nature of the alloy and its affinity toward the environment. The EDS and XRD analysis has evidently proved the presence of protective oxides formation on prolonged exposure at elevated temperature. The predominant oxide formed during the exposure at high temperature has a major contribution toward the protection of the samples. The nickel–iron-based superalloy is less prone to oxidation and hot corrosion when compared to the existing alloy in gas turbine engine simulating marine environment.

scholarly journals Mars™ SoLoNOx Combustion System CFD Modeling

1995 ◽  
Author(s):  
Matthew E. Thomas ◽  
Mark J. Ostrander ◽  
Andy D. Leonard ◽  
Mel Noble ◽  
Colin Etheridge
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Cfd Modeling ◽  
Cfd Analysis ◽  
Combustion System ◽  
Design Environment ◽  
Turbine Engine ◽  
Combustion Modeling ◽  
Premix Combustion ◽  
Industrial Gas Turbine

CFD analysis methods were successfully implemented and verified with ongoing industrial gas turbine engine lean premix combustion system development. Selected aspects of diffusion and lean premix combustion modeling, predictions, observations and validated CFD results associated with the Solar Turbines Mars™ SoLoNOx combustor are presented. CO and NOx emission formation modeling details applicable to parametric CFD analysis in an industrial design environment are discussed. This effort culminated in identifying phenomena and methods of potentially further reducing NOx and CO emissions while improving engine operability in the Mars™ SoLoNOx combustion system. A potential explanation for the abrupt rise in CO formation observed in many gas turbine lean premix combustion systems is presented.

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