Patent
Rotor blade damping structure for axial-flow turbine
TLDR
In an axial-flow turbine, at least one of the front and rear side contact surfaces of the axial flow turbine is formed at a certain angle with respect to a radial line connecting the rotor center and the contact surface as discussed by the authors.Abstract:
In an axial-flow turbine, at least one of front and rear side contact surfaces of shrouds (3a or 3b) of blades (1a or 1b) with respect to the turbine rotational direction is formed at certain angle with respect to a radial line connecting the rotor center and the contact surface. The shroud (3a) of the blade (1a) of a first kind is formed in a trapezoidal shape converging radially outward in cross section taken in a plane perpendicular to the turbine axial direction, and the shroud (3b) of the blade (1b) of a second kind is formed in an inverted trapezoidal shape converging radially inward in the cross section. Further, half of an angle (2α) between the front and rear side contact surfaces of the shrouds (3a or 3b) is made smaller than a static frictional angle of the contact surface. Since the shroud contact surfaces of two adjacent blades can be kept in pressure contact with each other under all operating conditions, a large dynamic stress reduction and superior damping properties can be obtained without producing excessive initial stresses at the blade airfoil and blade dovetail attachment portion.read more
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Patent
Mcraly bond coating and method of depositing said mcraly bond coating
Abdus Suttar Khan,Mohamed Nazmy +1 more
TL;DR: A method of depositing a bond coating to a surface of an article is described in this article, where the outer layer is more coarse than the inner layer, which is composed of a platinum type metal selected from the group consisting of platinum, palladium and rhodium.
Patent
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Donald W. Burns,John R. Louie +1 more
TL;DR: In this paper, a method for analyzing and designing structures with structural aliasing is presented, which applies in one embodiment of the present invention to structural systems which are cyclically symmetric.
PatentDOI
Apparatus for passive damping of flexural blade vibration in turbo-machinery
TL;DR: In this article, a rotor blade for a turbine engine rotor assembly is provided comprising a root, an airfoil, a platform, and a means for damping vibrations in the air foil.
Patent
Cooled snubber structure for turbine blades
TL;DR: A turbine blade assembly in a turbine engine as discussed by the authors includes a turbine blade and a first snubber structure, which extends outwardly from a sidewall of the turbine blade, and includes a hollow interior portion that receives cooling air from the internal cooling passage.
Patent
Snubber Assembly for Turbine Blades
TL;DR: In this article, a support structure for a rotatable turbine blade in a turbine engine is proposed, which is rigidly coupled to the first and second snubber structures, such that centrifugal loads exerted on the pressure and suctions sidewalls of the turbine blade caused by rotation thereof during operation of the engine are at least partially transferred to the support structure.
References
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Patent
Rotor blade assembly
TL;DR: In this paper, the rotor blade and disk structures enabling the disassembly and reassembly of a single rotor blade are described, particularly suited to configurations employing interlocking mid-span shrouds.
Patent
Guide vanes for supersonic turbine blades
TL;DR: In this article, guide vanes are installed between blades of the last stage of blading of a large steam turbine to form converging-diverging openings to minimize losses in this portion of the turbine.
Patent
Turbine blade with integral shroud
TL;DR: In this paper, a circular array of rotatable blades formed from blades having an integral shroud with a leading and a trailing planar surface, the leading surface being generally parallel to an axial radial plane passing through the center of the root of the blade and the trailing surface intersecting the axial radii to form an angle generally equal in degrees to 360 divided by the number of blades forming the circular array.
Patent
Blade retention feature for saddle fir tree root blades of turbo machines and method of using same
TL;DR: In the case of saddle-type rotor blades of axial-flow turbomachines, the locking blade (6a), without its root part engaging in the fir trees on the radially outer part of the rotor disk (1), is located under a large prestress between its neighboring blades (6b, 6c) as discussed by the authors.
Patent
Method of clamping blades
Pierre Meylan,Peter Novacek +1 more
TL;DR: In order to clamp blades (1, 2, n) of turbomachines to influence the blade vibration occuring in such machines, the shroud plates (1a, 2a, na) are dimensioned in such a way that they are in contact with one another in the installed condition without clearance and without contact force or else they exhibit a gap (3) relative to each other.