Patent
Gas turbine blade having a cooled shroud
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TLDR
In this paper, a gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade is shown to be cooled by cooling air passages formed within it.Abstract:
A gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade. The shroud is cooled by cooling air passages formed within it. A radial cooling air supply hole directs cooling air directly from the blade root through the airfoil and to the shroud. A plurality of cooling air passages extend from the supply hole and are disposed adjacent bearing surfaces along which the shroud contacts the shroud of an adjacent blade. One of these cooling air holes is formed in the portion of the shroud that projects from the convex surface of the airfoil and another one of the cooling air holes is formed in the portion of the shroud that projects from the concave surface of the airfoil. The cooling air holes extend to the edge of the shroud and discharge the cooling through an opening in the edge.read more
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Gas turbine moving blade
Yasuoki Tomita,Yukihiro Hashimoto,Kiyoshi Suenaga,Hisato Arimura,Shunsuke Torii,Jun Kubota,Akihiko Arai-cho Shirota,Sunao Aoki,Tatsuo Ishiguro +8 more
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References
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Patent
A coolable airfoil for a rotary machine
TL;DR: In this paper, a rotary airfoil for rotary machines is described with a spanwise extending leading edge passage connected to the trailing edge region by a chord-wisely extending tip passage.
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Rotor blade with cooled integral platform
TL;DR: In this article, a rotor blade (28) having a cooled integral platform (34) is described, which includes a plurality of first cooling holes (56, 58) for direct cooling of the rotor blades.
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Hollow turbine blade tip closure
James M Allen,Thomas M. Szewczuk +1 more
TL;DR: In this paper, an arrangement for closing selective areas of the tip portion of a hollow turbine blade having internal serpentine coolant passages is provided by radially extended wall portions at the tip of the blade along at least two sides of the outer ends of each two adjacent internal passages.
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Blade shank cooling arrangement
TL;DR: In this paper, an arrangement for cooling turbine blade shanks for gas turbines is presented, wherein a perforated chamber is arranged to cause a cooling fluid to impinge with a predetermined pattern upon inner wall surfaces of a shank portion of a turbine blade and/or the outer walls of adjacent turbine shanks.
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Gas turbine cooling systems
TL;DR: In this article, a gas turbine engine has a turbine with internally cooled, stationary nozzles incorporated into first and second stage nozzle segments and a system for supplying air to the nozzels, for effecting a flow of cooling air into impingement and film cooling relationships with a tip shoe mounted in the nozzle case, and for generating a flow which first impingements a nozzle case lip supporting the upstream ends of the second-stage nozzle segments.