NASA Transformational Tools and Technologies Project: 2700°F CMC/EBC Technology Challenge

2018 ◽  
Author(s):  
Janet Hurst
Keyword(s):  
High Temperature ◽  
Ceramic Matrix Composite ◽  
Performance Goal ◽  
Engine Operation ◽  
Materials Development ◽  
Turbine Engine ◽  
High Temperature Materials ◽  
Fuel Burn ◽  
Thermomechanical Testing ◽  
Engine Testing

Advanced gas turbine engine designs continue to push into regimes of higher operating temperatures and increased pressures. Materials capable of functioning under these extreme conditions have been sought by both government and industry. As part of its mission, the NASA Transformational Tools and Technologies (TTT) Project, under the auspices of NASA’s Aeronautics Research Mission Directorate (ARMD), has been pursuing high temperature materials development with the performance goal of 2700°F (1482°C) operation. This goal has evolved into a focused three year Technology Challenge which is nearing its conclusion. This challenge problem has sought to develop high temperature materials for turbine engines which will enable a 6% reduction in fuel burn for commercial aircraft as compared to the current generation. This ambitious effort has included ceramic matrix composite (CMC) compositions, architectures and processing as well as environmental barrier coating compositions (EBC) and processing routes. It has included collaborators and materials suppliers from both industry and academia. The development and validation of thermomechanical models and computational tools for design, analysis, and life prediction have been an important part of this effort. Evaluation of CMC/EBCs included various aspects of thermomechanical testing from coupon testing for strength and creep resistance, to materials evaluation under conditions similar to aspects of engine operation. Simulated engine testing of airfoil subcomponents in a P&W test rig is the final evaluation step following years of materials development. As this three year Technical Challenge concludes, plans are under development for continued environmental durability investigation of CMC/EBC systems accompanied by validated durability modeling.

scholarly journals Real-Time Fault Identification for Developmental Turbine Engine Testing

1997 ◽  
Author(s):  
Donald J. Malloy ◽  
Mark A. Chappell ◽  
Csaba Biegl
Keyword(s):  
Condition Monitoring ◽  
Fault Identification ◽  
Data Validation ◽  
Component Level ◽  
Engine Operation ◽  
Turbine Engine ◽  
Distributed Parallel Computing ◽  
Engine Testing ◽  
Engine Cycle ◽  
Engine Condition

Hundreds of individual sensors produce an enormous amount of data during developmental turbine engine testing. The challenge is to ensure the validity of the data and to identify data and engine anomalies in a timely manner. An automated data validation, engine condition monitoring, and fault identification process that emulates typical engineering techniques has been developed for developmental engine testing. An automated data validation and fault identification approach employing engine cycle-matching principles is described. Engine cycle-matching is automated by using an adaptive nonlinear component-level computer model capable of simulating both steady-state and transient engine operation. An automated model calibration process is also described. The model enables automation of traditional data validation, engine condition monitoring, and fault identification procedures. A distributed parallel computing approach enables the entire process to operate in realtime. The result is a capability to detect data and engine anomalies in realtime during developmental engine testing. The approach is shown to be successful in detecting and identifying sensor anomalies as they occur and distinguishing these anomalies from variations in component and overall engine aerothermodynamic performance.

Development and F-Class Industrial Gas Turbine Engine Testing of Smart Components With Direct-Write Embedded Sensors and High Temperature Wireless Telemetry

2008 ◽  
Author(s):  
David Mitchell ◽  
Anand Kulkarni ◽  
Edward Roesch ◽  
Ramesh Subramanian ◽  
Andrew Burns ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Condition Based Maintenance ◽  
Direct Write ◽  
Turbine Engine ◽  
Wireless Telemetry ◽  
Industrial Gas Turbines ◽  
Engine Testing ◽  
Industrial Gas Turbine

The potential for savings provided to worldwide operators of industrial gas turbines, by transitioning from the current standard of interval-based maintenance to condition-based maintenance may be in the tens of millions of dollars per year. Knowledge of the historical and current condition of life-limiting components will enable more efficient use of industrial gas turbine resources via increased operational flexibility, with less risk of unplanned outages as a result of off-parameter operations. To date, it has been impossible to apply true condition-based maintenance to industrial gas turbines because the extremely harsh operating conditions in the heart of a gas turbine preclude using the necessary advanced sensor systems to monitor the machine’s condition continuously. The U.S. Department of Commerce’s National Institute of Standards and Technology – Advanced Technology Program (NIST-ATP) awarded the Joint Venture team of Siemens Power Generation, Inc. and MesoScribe Technologies, Inc. a four-year, $5.4 million program in November, 2004, titled Conformal, Direct-Write-Technology-Enabled, Wireless, Smart Turbine Components. The target was to develop a potentially industry-changing technology to build smart, self-aware engine components that incorporate embedded, harsh-environment-capable sensors and high temperature capable wireless telemetry systems for continuously monitoring component condition in both the compressor and turbine sections. The approach involves several difficult engineering challenges, including the need to embed sensors on complex shapes, such as turbine blades, embedding wireless telemetry systems in regions with temperatures that preclude the use of conventional silicon-based electronics, protecting both sensors and wireless devices from the extreme temperatures and environments of an operating gas turbine, and successfully transmitting the sensor information from an environment very hostile to wireless signals. The program included full-scale, F-class industrial gas turbine engine test demonstrations with smart components in both the compressor and turbine sections. The results of the development program and engine testing to date will be discussed.

Impact of ENSIP on Engine Demonstrator Program

1986 ◽  
Author(s):  
T. E. Farmer
Keyword(s):  
Crack Propagation ◽  
Material Characterization ◽  
Structural Integrity ◽  
Damage Tolerance ◽  
Design Analysis ◽  
Materials Development ◽  
Turbine Engine ◽  
Customer Interface ◽  
Engine Testing

Incorporation of the Turbine Engine Structural Integrity Program (ENSIP) has provided a more organized and disciplined approach to the durability related aspects of the engine demonstrator program. As a result, engine capabilities are more easily related and the number of durability problems is reduced. This is accomplished by increased contractor/customer interface in the design analysis, material characterization and verification testing of the engine programs. The demonstrator program has been affected by the ENSIP requirements, particularly the Damage Tolerance aspects. The design analysis is more complex while the configurations tend to be simpler with fewer notched locations. Materials are developed for improved crack propagation life while component and engine testing is expanded to verify this capability. The ENSIP specification effects increases in analysis, materials development, verification testing and durability.

scholarly journals Cooled Cooling Air Systems for Turbine Thermal Management

1999 ◽  
Author(s):  
Greg B. Bruening ◽  
Won S. Chang
Keyword(s):  
High Temperature ◽  
Heat Exchanger ◽  
Thermal Management ◽  
Positive Impact ◽  
Engine Performance ◽  
Turbine Engine ◽  
High Temperature Materials ◽  
Potential Impact ◽  
Design Tradeoffs ◽  
Cooling Air

This paper evaluates the feasibility and potential impact on overall engine performance when utilizing the heat sink sources available in a gas turbine engine for improved turbine thermal management. A study was conducted to assess the application of a heat exchanger to cool the compressor bleed air normally used air for cooling turbine machinery. The design tradeoffs of this cooled cooling air approach as we’ll as the methodology used to make the performance assessment will be addressed. The results of this study show that the use of a cooled cooling air (CCA) system can make a positive impact on overall engine performance. Minimizing the complexity and weight of the CCA system, while utilizing advanced, high temperature materials currently under development provide the best overall solution in terms of design risk and engine performance.

Engine Testing for the Demonstration of a 3D-Woven Based Ceramic Matrix Composite Turbine Vane Design Concept

2018 ◽  
Author(s):  
Fumiaki Watanabe ◽  
Takashi Manabe
Keyword(s):  
Ceramic Matrix Composite ◽  
Design Concept ◽  
Woven Fabric ◽  
Aircraft Engines ◽  
Weak Point ◽  
Turbine Engine ◽  
Turbine Vanes ◽  
Turbine Vane ◽  
Engine Testing ◽  
Industrial Gas Turbine

In this paper, the authors present a solid vane concept which uses 3D woven fabric based SiC/SiC CMC and the result of engine testing which was conducted to demonstrate this concept. The authors devised a design concept, in which a vane is made from a folded woven, for the uncooled turbine vanes of the aircraft engines. The advantage of this concept is that there is no structural weak point because a whole vane including outer / inner platform consists of one continuous woven. In order to demonstrate the applicability of this concept to the actual engine parts, CMC turbine vanes were tested with IHI-IM270 that is a small industrial gas turbine engine. After 862 hour testing, there was no defect such as cracks, wear, and deformation.

Thermochemical Protection of High Temperature Materials

2001 ◽  
Vol 8 (4) ◽  
pp. 231-241 ◽  
Author(s):  
J. Stricker ◽  
Y. Goldman ◽  
Genady Borodyanski
Keyword(s):  
High Temperature ◽  
High Temperature Materials

3D Structural Analysis of Selected High-Temperature Materials

2018 ◽  
Vol 55 (7) ◽  
pp. 424-446
Author(s):  
U. Jäntsch ◽  
M. Klimenkov ◽  
A. Möslang ◽  
F. Reinauer ◽  
J. Reiser ◽  
...  
Keyword(s):  
High Temperature ◽  
Structural Analysis ◽  
High Temperature Materials

ULTEM 6100, ULTEM 6200, ULTEM 6202

Alloy Digest ◽  
1990 ◽  
Vol 39 (7) ◽  
Keyword(s):  
Fracture Toughness ◽  
Corrosion Resistance ◽  
Shear Strength ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
High Temperature Materials ◽  
Electrical Components

Abstract ULTEM 6100 and 6200 are glass reinforced and ULTEM 6202 is a mineral filled copolymer resin. For properties of the unreinforced resin, ULTEM 6000, see Alloy Digest P-27, June 1991. These are high temperature materials that are particularly suitable for military electrical components which must survive 200 C testing. This datasheet provides information on physical properties, hardness, tensile properties, and compressive and shear strength as well as fracture toughness. It also includes information on corrosion resistance. Filing Code: Cp-16. Producer or source: G. E. Plastics.

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