Compressor coating effects on gas turbine engine performance

Journal Article · Tue Oct 01 00:00:00 EDT 1991 · Journal of Engineering for Gas Turbines and Power; (United States)

DOI:https://doi.org/10.1115/1.2906273· OSTI ID:5135084

MacLeod, J D ^[1]; Laflamme, J C ^[2]

---

1. National Research Council, Ottawa, Ontario K1A 0R6 (CA)
2. 421 Tactical Fighter Squadron, Canadian Forces Europe, CFB Baden-Soelingen (DE)

In an attempt to increase the time between maintenance actions and to improve performance retention of turboprop engines installed in transport and maritime patrol aircraft, the Canadian Department of National Defence is evaluating an erosion and corrosion-resistance blade coating, for use on compressors. As coatings could appreciably alter engine performance by virtue of their application thickness and surface quality, the National Research Council of Canada was asked to quantify any performance changes that could occur. A project was initiated, utilizing a new Allison T56 turboprop engine, to assess not only the performance changes resulting from the coating, but also those from dismantling and reassembling the compressor, since the compressor must be completely disassembled to apply the coating. This paper describes the project objectives, the experimental installation, and the measured effects of the coating application on compressor performance.

• OSTI ID: 5135084
• Journal Information: Journal of Engineering for Gas Turbines and Power; (United States), Vol. 113:4; ISSN 0742-4795
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
36 MATERIALS SCIENCE
COMPRESSOR BLADES
MATERIALS TESTING
GAS COMPRESSORS
COATINGS
GAS TURBINE ENGINES
PERFORMANCE TESTING
CORROSION PROTECTION
CORROSION RESISTANCE
COMPRESSORS
ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
TESTING
330103* - Internal Combustion Engines- Turbine
360105 - Metals & Alloys- Corrosion & Erosion