Peter E. Voyer - Tolland CT Thomas C. Walsh - New Britain CT Joseph Grzyb - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B23P 1500
US Classification:
291564R
Abstract:
The method disclosed herein is the improved construction of an engine split case by electron beam welding the mating flanges to the split case cylinder where the outer diameter of the case includes "L" shaped rails and radial circumferential flanges.
Keith T. Honda - Manchester CT Stephen L. Smith - South Windsor CT Peter E. Voyer - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 530 F01D 522 F01D 532
US Classification:
416219R
Abstract:
Rotor blade and disk structures enabling the disassembly and reassembly of a single rotor blade are disclosed. The concepts are particularly suited to configurations employing interlocking mid-span shrouds which inhibit the withdrawal of a single blade from a disk. In one specific geometry the rotor blade root section (20) and the disk attachment slot (24) are contoured to provide increasing clearance between the bottom of the blade root section and the attachment slot as the blade is withdrawn axially from the slot. Rocking of the blade within the provided clearance enables withdrawal of the blade around the shroud segments (30,32) and airfoil sections (16) of the adjacent blades (12).
Edmund D. Trousdell - Tolland CT Peter E. Voyer - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 530
US Classification:
416215
Abstract:
A rim seal for blocking the leakage of working medium gases between an array of rotor blades and a rotor disk is disclosed. Various construction details which provide positive contact between the seal and the disk are developed. The rim seal of the present invention is of the ladder-type having application to a disk adapted by a circumferential groove to receive the rotor blades.
Gary P. Peters - Lebanon CT Robert L. Rowley - Glastonbury CT Peter E. Voyer - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 506
US Classification:
416198A
Abstract:
A lightweight, rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is disclosed. Various construction details which enhance the axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed. The rotor assembly employs a frustoconical member to connect a shaft to the disk.
Method For Manufacturing A Split Engine Casing From A Cylinder
Thomas C. Walsh - New Britain CT Peter E. Voyer - Tolland CT Francis J. Wallace - Windsor CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B23P 1500
US Classification:
29418
Abstract:
The method of fabricating a jet engine casing into two removable halves is disclosed. The method includes turning a cylindrical blank to obtain the radial structural ribs, diametrically slotting axially the outer diameter to receive two mating flanges and boring the inside diameter to remove sufficient material to expose the inner edge of the mating flanges whereby the casing is split along the axial axis.
Alan D. Munroe - Glastonbury CT Peter E. Voyer - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 1108
US Classification:
415174
Abstract:
An abradable rub strip for use in the compression section of a gas turbine engine is disclosed. Various construction details are developed for limiting penetration of the abradable rub strip by an array of rotor blades. A ring formed of metallic material is embedded in the abradable rub strip.
Keith T. Honda - Manchester CT Stephen L. Smith - South Windsor CT Peter E. Voyer - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 530
US Classification:
416219R
Abstract:
Rotor blade and disk structures enabling the disassembly and reassembly of a single rotor blade are disclosed. The concepts are particularly suited to configurations employing interlocking mid-span shrouds which inhibit the withdrawal of a single blade from a disk. In one specific geometry the rotor blade root section (20) and the disk attachment slot (24) are contoured to provide increasing clearance between the bottom of the blade root section and the attachment slot as the blade is withdrawn axially from the slot. Rocking of the blade within the provided clearance enables withdrawal of the blade around the shroud segments (30,32) and airfoil sections (16) of the adjacent blades (12).
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