1-20 of 485 Search Results for

Turbine blades

Follow your search
Access your saved searches in your account

Would you like to receive an alert when new items match your search?
Close Modal
Sort by
Image
Published: 01 January 2006
Fig. 8 Two shipboard turbine blades. Pressure side shown facing out of the page. Arrows denote areas where heavy corrosion products are observed. More
Image
Published: 01 January 2006
Fig. 11 Microstructures of nickel-base Alloy 713C turbine blades. (a) Original structure prior to service. (b) Coarsening of γ' precipitates and elimination of secondary γ' caused by 5000 h of service More
Image
Published: 01 June 2016
Fig. 1 Macrostructure of three turbine blades: polycrystalline (left), columnar grain directionally solidified (center), and single-crystal directionally solidified (right) More
Image
Published: 01 January 1990
Fig. 3 The evolution of the processing of nickel-base superalloy turbine blades. (a) From left, equiaxed, directionally solidified, and single-crystal blades. (b) An exposed view of the internal cooling passages of an aircraft turbine blade. Source: Ref 5 More
Image
Published: 01 January 2002
Fig. 11 Hot corrosion attack of René 77 nickel-base alloy turbine blades. (a) Land-based, first-stage turbine blade. Notice deposit buildup, flaking, and splitting of leading edge. (b) Stationary vanes. (c) A land-based, first-stage gas turbine blade that had type 2 hot corrosion attack. (d More
Image
Published: 01 January 2002
Fig. 12 Heat-damaged turbine blades. (a) Heat-damaged first- or second-stage turbine blade (A), which remained intact but with a darkened appearance. It is common to have blades that appear to be in relatively good condition but with an underlying overtemperature condition. (b) Two third-stage More
Image
Published: 01 January 2002
Fig. 13 Flow diagram for remaining life assessment of gas turbine blades More
Image
Published: 01 January 2002
Fig. 14 Sectioning of turbine blades for metallographic examination. (a) Typical locations for cross sectioning of turbine blades. (b) View of Sectioned blade More
Image
Published: 30 August 2021
Fig. 12 (a) Photograph showing one of the intact steam turbine blades from the failed stage. The arrow indicates the fracture location. (b) Photograph of the fracture surface. Scale: millimeters. (c) Scanning electron fractograph of the initiation region showing a mixed transgranular More
Image
Published: 30 August 2021
Fig. 28 (a) Photograph of fourth-stage turbine blades prior to removal. The first blade to fail is indicated with an arrow; an exhaust thermocouple is shown in the foreground. (b) Photograph of blade fracture surface after sectioning. Note the blue discoloration at the trailing edge. (c More
Image
Published: 30 August 2021
Fig. 4 Failed second-stage turbine blade. (a) Photograph of failed blade, with fracture at the top of the image. (b) Stereomicroscopic image of fracture surface showing coarse, intergranular topology. (c) Scanning electron fractograph showing void coalescence on fracture surface. (d) Optical More
Image
Published: 01 January 2006
Fig. 10 Close-up of failed turbine blade. Cracking has initiated at platform/stem transition where corrosion has occurred. Original magnification 20× More
Image
Published: 01 January 2006
Fig. 11 Crack propagation direction of failed turbine blade. Corrosion propagates over 60% of the stem wall, thus increasing the applied stresses in the remaining stem wall. Fracture shows a sharp transgranular characteristic suggesting cleavage or high cycle fatigue. Original magnification 55× More
Image
Published: 01 January 2006
Fig. 9 Tip cracking of a directionally solidified MAR-M-246 turbine blade More
Image
Published: 01 January 2006
Fig. 27 High-temperature oxidation of the tip of an industrial gas turbine blade. Below the tip, a coating is protecting the base metal. See the article “Corrosion of Industrial Gas Turbines” in this Volume. More
Image
Published: 01 January 2006
Fig. 28 Severe attack of an aeroderivative gas turbine blade by hot corrosion. See the article “Corrosion of Industrial Gas Turbines” in this Volume. More
Image
Published: 01 January 2006
Fig. 5 Severe attack of an aeroderivative gas turbine blade by hot corrosion More
Image
Published: 01 January 1990
Fig. 2 Advances in turbine blade materials and processes since 1960. Source: Ref 4 More
Image
Published: 01 January 1990
Fig. 2 Directionally solidified turbine blade CM 247 LC More
Image
Published: 01 January 1990
Fig. 4 CM 247 LC directionally solidified turbine blade, as-cast, and supersolutioned microstructures, heat V6692. Micrographs taken from airfoil, transverse orientation. (a) As-cast. 90×. (b) As-cast. 905×. (c) Supersolutioned. 90×. (d) Supersolutioned. 905× More