Patent
Compressor blade tip seal
TLDR
In this article, the inner wall surrounding the tips of axial flow fan/compressor blades in a turbine type power plant is angularly disposed relative to the gas path wall to allow deeper penetration into the trench and minimize leakage around the tips.Abstract:
The trench inner wall surrounding the tips of axial flow fan/compressor blades in a turbine type power plant is angularly disposed relative to the gas path wall to allow deeper penetration into the trench and minimize leakage around the tips. Gap closure between the inner wall of the trench and tip is contemplated by the contour of the blade/trench.read more
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Patent
Fan and shroud assembly
TL;DR: In this article, a fan and shroud assembly includes a fan with a hub rotating around one shaft and a plurality of blades extending outwardly from the hub, a shroud encompassing the fan to adjust airflow by rotation of the fan, and a guide ring portion located at a position where a predetermined gap exists between the shroud and a circumference connecting end tips of the blades so that the fan coupled to the shroud rotates, and each swirl prevention unit having a shape in which the length of a circular arc passing each of the swirl prevention units with respect to the center of the shroud decreases as the
Patent
Shroud ring for an axial flow turbine
TL;DR: In this article, the rotor blades are fitted with circumferential shroud plates, which seal by virtue of serrations against the casing by the formation of radial gaps (16, 17, 18, 19).
Patent
Shroud band for an axial-flow turbine
TL;DR: In this article, the stator is divided into at least two axially staggered cavities at the labyrinth inlet and a curved sealing strip which runs at least approximately horizontally runs on each step of the shroud plate.
Patent
Airfoil and corresponding guide vane, blade, gas turbine and turbomaschine
Andrew Shepherd,Philip Twell +1 more
TL;DR: In this article, an airfoil is arranged in a compressor section of a gas turbine and a tip region is configured such that the tip region (29) is located between the pressure surface and the suction surface opposite to the platform (25) in respect of the pressure and suction surfaces.
Patent
Gas turbine engine casing and rotor blade arrangement
TL;DR: In this article, an arrangement for a gas turbine engine consisting of a compressor and its surrounding casing is described, where the inner casing has a generally cylindrical inner surface with a circumferential array of recesses.
References
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Patent
Blade tip shroud for a compression stage of a gas turbine engine
TL;DR: In this article, a blade tip shroud structure for a compression stage of a gas turbine engine is described and various concepts relating to shroud designs and their influence on blade performance are discussed.
Patent
Blade tip seal for an axial flow rotary machine
TL;DR: In this article, an airfoil tip seal structure for axial flow rotary machines is described and various concepts relating to seal designs and their influence on tip sealing effectiveness are discussed.
Patent
Labyrinth seal for axial flow fluid machines
TL;DR: In this paper, a sealing device in a turbine for preventing excessive leakage of motive fluid between a stator and the tips of rotor blades, the leakage being from a high pressure side to a low-pressure side, including an airfoil provided on the outer periphery of each rotor blade with the air foil being skewed to pump the leakage fluid back to the high pressure.
Patent
Compressor casing recess
TL;DR: In this paper, the aerodynamic efficiency of axial flow turbomachines has been investigated and a means for improving the efficiency of the compressor of a turbomachine is described.