Published May 25, 2002 | Version v1
Journal article Metadata-only

Ultrasonic evaluation of the effects of compressive residual stresses on aircraft engine turbine blades subjected to high cycle fatigue

Creators

  • 1. Don E. Bray, Inc., P.O. Box 10315, College Station, Texas 77842-0315 (United States)
  • 2. General Electric Aircraft Engines, Cincinnati, Ohio 45215 (United States)
  • 3. Engineering and Testing, College Station, Texas 77841 (United States)

Description

Experiments conducted on titanium (Ti-64) turbine blades with the LCR ultrasonic wave at 20 MHz showed significant differences in untreated blades and blades treated to increase the subsurface compressive residual stress. Group 1 showed significant differences in the treated and untreated areas, the top and bottom of the blades, high cycle fatigue and cracked and uncracked conditions. Group 2 blades showed significant difference between untreated and treated travel-times at probes located at the blade leading edge

Additional details

Identifiers

DOI
10.1063/1.1472990;

Publishing Information

Journal Title
AIP Conference Proceedings
Journal Volume
615
Journal Issue
1
Journal Page Range
p. 1643-1650
ISSN
0094-243X
CODEN
APCPCS

Conference

Title
28. annual review of progress in quantitative nondestructive evaluation
Dates
29 Jul - 3 Aug 2001
Place
Brunswick, ME (United States)

INIS

Country of Publication
United States
Country of Input or Organization
International Atomic Energy Agency (IAEA)
INIS RN
35081862
Subject category
S36: MATERIALS SCIENCE;
Resource subtype / Literary indicator
Conference
Descriptors DEI
AIRCRAFT; ENGINES; FATIGUE; MHZ RANGE 01-100; RESIDUAL STRESSES; TITANIUM ALLOYS; TURBINE BLADES; ULTRASONIC TESTING; ULTRASONIC WAVES
Descriptors DEC
ACOUSTIC TESTING; ALLOYS; FREQUENCY RANGE; MATERIALS TESTING; MECHANICAL PROPERTIES; MHZ RANGE; NONDESTRUCTIVE TESTING; SOUND WAVES; STRESSES; TESTING; TRANSITION ELEMENT ALLOYS

Optional Information

Notes
(c) 2002 American Institute of Physics.