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aircraft engine

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Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270074
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter discusses the key findings of an investigation into the failure of an aircraft engine fuel pump. It explains how investigators came to the conclusion that metal slivers from a heavily worn spring may have interrupted the flow of lubricant to one of the slipper...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270087
EISBN: 978-1-62708-301-0
...Abstract Abstract A turbine blade in an aircraft engine failed, fracturing at the root above the fir tree region. Fractography indicated that a fatigue crack initiated at the trailing edge of the blade and the final fracture occurred when the crack reached critical length. Although the exact...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270095
EISBN: 978-1-62708-301-0
...Abstract Abstract A pair of bearings mounted side by side in an aircraft engine failed in service. Photographs show that the inner rings were either broken or deformed, the balls were worn and flattened, and the cages severely damaged. The bearing races were damaged as well, but only on one...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270097
EISBN: 978-1-62708-301-0
...Abstract Abstract Metal particles were frequently detected in the oil of an aircraft engine, triggering an investigation that led to a torque sensor and its mounting components. The sensor assembly was removed and examined in greater detail. As the chapter explains, investigators discovered...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270102
EISBN: 978-1-62708-301-0
...Abstract Abstract A design modification intended to reduce dowel bolt failures in an aircraft engine proved ineffective, prompting an investigation to determine what was causing the bolts to break. As the chapter explains, failure specimens were examined under various levels of magnification...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270115
EISBN: 978-1-62708-301-0
... Background Visual Examination of General Physical Features Testing Procedure and Results Two compressor rotors of an aircraft engine sustained severe damage during operation. In both rotors, several blades got sheared off with some blades lifted from the dovetail portion of the drum. Several...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270118
EISBN: 978-1-62708-301-0
...Abstract Abstract A first-stage compressor blade failed prematurely in an aircraft engine, fracturing at the midpoint of the root transition region. An examination of the fracture surface revealed beach marks, striations, and pitting, indicating that the blade failed by fatigue due to a crack...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270126
EISBN: 978-1-62708-301-0
...Abstract Abstract A test flight was cut short after a fire warning came on indicating a problem with one of the four engines on an aircraft. A visual examination following the precautionary landing revealed several burned hoses, a melted bolt, and fuel leaking from the base of the main burner...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270128
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter discusses the failure of a first-stage compressor blade in an aircraft engine and explains how investigators determined that it was caused by fatigue, with a crack originating from corrosion pits that developed in the root transition region on the convex side...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270133
EISBN: 978-1-62708-301-0
...Abstract Abstract A second-stage compressor blade in an aircraft engine fractured after 21 h of service. The remaining portion of the blade was removed and examined as were several adjacent blades. Based on the results of SEM fractography, microstructural analysis, and hardness testing...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270135
EISBN: 978-1-62708-301-0
...Abstract Abstract A second-stage turbine blade in an aircraft engine failed in service, fracturing along a path through the shroud hole. Cracks were also found in the shroud holes of the two adjacent blades. Based on the results of visual examination and SEM fractography, investigators...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270138
EISBN: 978-1-62708-301-0
...Abstract Abstract A high-pressure turbine blade in an aircraft engine failed prematurely, fracturing close to the root. Visual examination revealed significant plastic deformation on the leading edge of the blade, blocky cleavage on the trailing edge, and a region covered with fissures...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270141
EISBN: 978-1-62708-301-0
... A compressor blade made of titanium alloy failed during testing of an aircraft engine. The blade material and the processing conditions of the blade were found to be satisfactory. Macro, micro, and electron fractographic investigations showed that the blade had failed by an impact load acting on its concave...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270148
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter describes an investigation that was conducted to determine why quill shafts were failing prematurely in gear boxes on aircraft engines. The investigation focused on the splines in a splined bore. Visual examination showed that the splines were heavily worn...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270150
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter discusses the failure of a compressor blade in an aircraft engine and explains how investigators determined the cause. Based on visual examination and the results of SEM fractography and chemical analysis, it was concluded that blade failed due to fatigue fracture...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270160
EISBN: 978-1-62708-301-0
...Abstract Abstract The nose bullet of an aircraft engine developed a crack and was removed and examined to determine the cause. The bullet was made from a titanium alloy and was of welded construction. Close-up views show that the crack originated in an area of rework along the weld seam...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270168
EISBN: 978-1-62708-301-0
...Abstract Abstract During cyclic spin tests, the turbine disc in an aircraft engine broke apart with a loud noise, followed by a fire. Based on a detailed examination and the results of SEM fractography and hardness measurements, failure analysts concluded that a locking plate became dislodged...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270172
EISBN: 978-1-62708-301-0
...Abstract Abstract During a routine preflight inspection of a piston aircraft engine, part of a cooling fin was found that had broken off the cylinder. The piece, made of aluminum-silicon alloy, was cleaned and examined. Based on the fracture characteristics revealed by an electron microscope...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270173
EISBN: 978-1-62708-301-0
...Abstract Abstract A titanium alloy disc on the fourth stage of an aircraft engine compressor was found cracked in the course of a defect investigation. The disc had not yet reached the halfway point of its expected service life. The chapter explains how the crack was examined and provides...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270177
EISBN: 978-1-62708-301-0
...Abstract Abstract A driven gear in the gear box of an aircraft engine fractured after a 40 h test run. The driving gear and gear shaft were also damaged. Based on the results of fractography, chemical analysis, metallography, and hardness testing, the fracture was caused by a fatigue crack...