United Technologies Corporation

Other

Hans R Przirembel

Friedrich O Soechting

Thomas A Auxier

Scott Alan Przirembel

George P Liang

William S Kvasnak

Kenneth K Landis

Christopher Charles Williams

William A Moore

Timothy J Remley

J Tyson Balkcum, Iii

Robert C Meyer

A hairbrush includes a body having a first half and a second half, and a container therebetween for storing fluids like liquids, i.e., water, alcohol, lotions, creams, etc. The first half and second half include respective bottom parts of a generally rectangular configuration each extending to an elongated portion extending to an open front. The first half and second half include respective inner surfaces and outer surfaces, with the second half including a flexible core from which a plurality of bristles extend radially outwardly.

Liquid dispensing hair brush

A shoe tree includes a body having a toe member that has a distal tip end and a proximal end. The toe member is insertable into a toe portion of a respective shoe and formed to support the toe portion of the shoe. The shoe tree also includes a heel member that is insertable into a heel portion of the respective shoe and formed to support the heel portion thereof. The body is hollow inside and presents a neck portion of tubular member to receive and store fluids like liquids to add weight to the shoe tree to spread the weight of the shoe tree to the respective shoe to keep the shoe in shape at all times.

Shoe tree

An internally-cooled turbomachine element has an airfoil extending between inboard and outboard ends. A cooling passageway is at least partially within the airfoil and has at least a first turn. Means are in the passageway for limiting a turning a loss of the first turn. The turbomachine element may result from a reengineering of an existing element configuration lacking such means.

Cooling passageway turn

The present invention relates to a lightweight shrouded turbine blade. The turbine blade comprises an airfoil section and a hollow blade tip shroud joined to the airfoil section. The hollow tip shroud is preferably a cast, compartmentalized structure and has a plurality of ribs acting as load bearing structures and defining a plurality of shroud core sections. Each of the shroud core sections communicates with a supply of cooling fluid and has a plurality of apertures for supplying cooling fluid to exterior portions of the shroud.

Thin walled cooled hollow tip shroud

A hollow airfoil is provided having a pressure side wall, a suction side wall, a cavity formed between the pressure and suction side walls, a plurality of cooling ports disposed within the pressure side wall, and a plurality of passages, each extending between the cavity and one of the cooling ports. Each passage has a first wall adjacent the suction side wall, a pair of passage side walls extending substantially toward the pressure side wall, and a second wall adjacent the pressure side wall. In a first embodiment, each passage further includes a pair of fillets extending between the passage side walls and the second wall. In a second embodiment, each passage includes a jog adjacent each cooling port.

Trailing edge cooling apparatus for a gas turbine airfoil

The method of manufacturing an air cooled stator vane for a gas turbine engine by casting an inner shell with suction side wall and pressure side wall of the airfoil, stamp forming from a blank sheet metal a pair of sheaths and attaching one sheath of the pair of sheaths to the suction side wall and the other sheath of the pair of sheaths to the pressure side wall. Forming in the step of stamp forming pockets with a slot at the end of each pocket for flowing a film of cooling air over the exterior of each of the pair of sheaths and drilling holes in the end of the pocket remote from the slot prior to the step of joining to fluidly connect the pocket with cooling air. The method includes in another embodiment sheet metal blank stamp formed with a corrugated member and attaching it between the cast pressure side wall and one sheath of the pair sheaths and between the suction side wall and the other sheath of the pair of sheaths and drilling holes prior to the step of attaching in the high points of the corrugated member. In another embodiment the method includes forming perforated cylindrically shaped inserts and attaching the inserts in the central passageway formed in the cast inner shell.

Method of making an air cooled vane with film cooling pocket construction

An air cooled stator vane or the like for a gas turbine engine is constructed to include a plurality of axially and radially spaced pockets formed on the outer surfaces of the airfoil sections. Air is directed into the pocket on one end of a passage defined by the pocket to impinge on the back wall of the pocket, change directions and flow through the passage and discharge into the gas path as a film of cooling air coalesced by slots formed at the end of the pocket. The outer wall can be cast in its entirety or fabricated from sheet metal sheaths supported to a cast inner shell. The pockets are fed cooling air through a central passage in the stator vane or through impingement inserts disposed in the central passage.

Cooled vane

An air cooled stator vane for a gas turbine engine is fabricated by casting the suction side wall and pressure side wall of the airfoil into separate halves and joining both halves at complementary sides and ribs, and forming pockets with a slot at the end of each pocket for flowing a film of cooling air over the exterior wall and drilling holes in the end of the pocket remote from the slot to fluidly connect the pocket with cooling air. The method includes in another embodiment a sheet metal sheath with pockets and slots identical to the pockets and slots in the shell configuration formed over the shell. Another embodiment includes perforated inserts extending in the cavity formed by the shell.

Method of manufacturing an air cooled vane with film cooling pocket

A stator vane for a gas turbine engine wherein the airfoil section includes a plurality of pockets with an impingement hole at the upstream end of a passageway formed in the pocket and a slot formed on the opposite end of the pocket for discharging a film of cooling air along the outer surface of the air foil. The impingement hole and slot being arranged so that the flow of air in the passageway is in counterflow indirect heat exchange relationship with the gas path, thus placing the hottest part of the metal forming the pocket with the coolest air in the pocket.

A convectively cooled turbine blade has two distinct cooling air passage systems. The first system cools the blade leading edge and emits cooling air through outlet passageways in the leading edge arranged in showerhead array. The second system includes a three-pass series flow passage through the remainder of the blade. Air flow from the second system emits along the trailing edge through an array of slots generally configured in the form of a Venetian blind.

Turbine blade

A turbomachinery vane or blade with cooled platforms including provision for film cooling the inner and outer surfaces of the platform forward portion, including cooling fluid cavities in the platform on both the pressure and suction sides of the vane or blade airfoil for cooling this region of the platform by a combination of impingement, convection and film cooling, and a selective array of drilled holes extending through the platform trailing edge for convection cooling thereof.

Growing community of inventors

Jupiter, FL, United States of America

Hans R Przirembel