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Title: Project 1 Update Meeting; Pratt & Whitney Export Version.

Abstract

Abstract not provided.

Authors:
; ; ; ;
Publication Date:
Research Org.:
Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
Sponsoring Org.:
USDOE National Nuclear Security Administration (NNSA)
OSTI Identifier:
1368513
Report Number(s):
SAND2016-6339PE
643440
DOE Contract Number:
AC04-94AL85000
Resource Type:
Conference
Resource Relation:
Conference: Proposed for presentation at the Videoconference.
Country of Publication:
United States
Language:
English

Citation Formats

Jerome, Trevor, Smith, Scott A, Brake, Matthew Robert, Damien Lancereau, and Tilan Dossogne. Project 1 Update Meeting; Pratt & Whitney Export Version.. United States: N. p., 2016. Web.
Jerome, Trevor, Smith, Scott A, Brake, Matthew Robert, Damien Lancereau, & Tilan Dossogne. Project 1 Update Meeting; Pratt & Whitney Export Version.. United States.
Jerome, Trevor, Smith, Scott A, Brake, Matthew Robert, Damien Lancereau, and Tilan Dossogne. 2016. "Project 1 Update Meeting; Pratt & Whitney Export Version.". United States. doi:. https://www.osti.gov/servlets/purl/1368513.
@article{osti_1368513,
title = {Project 1 Update Meeting; Pratt & Whitney Export Version.},
author = {Jerome, Trevor and Smith, Scott A and Brake, Matthew Robert and Damien Lancereau and Tilan Dossogne},
abstractNote = {Abstract not provided.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = 2016,
month = 7
}

Conference:
Other availability
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  • A Pratt and Whitney Aircraft Group program begun in 1978 has led to the development of retrofit kit packages and major engine modifications that will provide thrust-specific fuel consumption (TSFC) reductions of 2.1% for the JT8D-1 and -7 engines, 3.0% for the JT8D-9 engine, and 5.5% for the JT8D-15, -17, and -17R engines under cruise conditions, and comparable fuel savings under other conditions. The modifications being made will affect the fan, compressor, and turbine sections of the engines to improve component efficiency. The retrofit kits will be used on existing in-service engines; other modifications will be introduced in service duringmore » 1981 and 1982. Fuel savings per engine per year could range from 27,000 to 91,000 gal, and fleet savings could amount to several hundred million gallons per year.« less
  • Thermal barrier coatings (TBCs) will be used to achieve the objectives of the Advanced Turbine Systems (ATS) program. They are used in aircraft engines and have accumulated millions upon millions of reliable hours. Differences in the duty cycles of the aircraft and industrial gas turbines are recognized as is the marked differences in environmental operational envelope. At the completion of this program the TBCs best suited to meet the needs of the ATS program will have been identified, tested, and confirmed.
  • Pratt and Whitney has accumulated over three decades of experience with thermal barrier coatings (TBC). TBC`s were originally developed to reduce surface temperatures of combustors of JT8D gas turbine engines to increase the thermal fatigue life of the components. Continual improvements in design, processing and properties of TBC`s have extended their applications to other turbine components such as vanes, vane platforms and blades with attendant increases in performance and component durability. Plasma spray based generation 1 (Gen 1) combustor TBC with and w/o yttria partially stabilized zirconia deposited by air plasma spray (APS) on an APS NiCoCrAlY bond coat continuesmore » to perform extremely well in all product line engines. Durability of this TBC has been further improved in Gen 2 TBC for vanes by incorporating low pressure chamber plasma sprayed (LPPS) NiCoCrAlY as a bond coat. The modification has improved TBC durability by a factor of 2.5 and altered the failure mode from a `black failure` within the bond coat to a `white failure` within the ceramic. Further improvements have been accomplished by instituting a more strain tolerant ceramic top layer with electron beam physical vapor deposition (EB-PVD) processing. This Gen 3 TBC has demonstrated exceptional performance on rotating airfoils in high thrust rated engines by improving blade durability by 3x, by eliminating blade creep, fracture and rumpling of metallic coatings used for oxidation protection of the airfoil surfaces. A TBC durability model for plasma sprayed as well as EB-PVD systems is proposed which involves the accumulation of compressive stresses during cyclic thermal exposure. The model attempts to correlate failure of the various TBCs with elements of their structure and its degradation with thermocyclic exposure.« less
  • The objective of the Advanced Turbine Systems (ATS) Program is to develop ultra-high efficient, environmentally superior, and cost competitive gas turbine systems. The operating profiles of these industrial gas turbines are long, less cyclic with fewer transients-compared with those for aircraft gas turbine engines. Therefore, creep rather than thermal fatigue, becomes primary life-limiting for hot section components. Thermal barrier coatings (TBCs) will be used to achieve the objectives of the program. TBCs allow surface temperatures to increase without compromising the structural properties of the alloy. TBCs typically consist of a ceramic insulating layer, deposited onto the substrate with an interveningmore » metallic layer, which imparts oxidation protection to the substrate and provides a surface to which the ceramic layer can adhere.« less