General Electric Company

Other

David M Kercher

Nesim Abuaf

John Howard Starkweather

Dean Thomas Lenahan

Iain Robertson Kellock

Kevin Joseph Barb

Sanjay Chopra

Douglas Arthur Lupe

Sankar Nellian

A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.

Bucket platform cooling scheme and related method

A turbine airfoil includes a leading edge, a trailing edge, and a root and tip spaced apart along a span axis. First and second airfoil sides extend therebetween. A cooling circuit is disposed between the sides for channeling a cooling fluid. A plurality of diffusion fan holes are spaced apart along the span axis in the airfoil first side, with each fan hole increasing in flow area between an inlet at the cooling circuit and an outlet on the airfoil first side disposed coaxially about a centerline fan axis. The fan axis is inclined at an acute span angle, with the outlet being greater in span height than the inlet, and substantially equal in width for increasing coverage of the outlets and film cooling air therefrom along the span axis.

Spanwise fan diffusion hole airfoil

A turbine airfoil includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The tip includes a floor bounding an internal cooling channel within the airfoil which channels cooling air. The airfoil tip includes a first rib adjacent the pressure sidewall, a second rib spaced therefrom to define a first slot, and a third rib adjacent the suction sidewall to define a second slot with the second rib. The tip floor includes feed holes extending between the cooling channel and the first slot for supplying cooling air therein for discharge over the second rib towards the third rib.

Triple tip-rib airfoil

A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the internal passage from at least one of the first and second sides. An auxiliary turbulator rib is spaced between adjacent ones of the primary ribs. The auxiliary rib has a height which is less than the height of the primary ribs for augmenting convective heat transfer enhancement with reduced pressure loss, and, therefore, reduced cooling air requirements.

Turbine blade having auxiliary turbulators

A gas turbine engine turbine blade and method of manufacture includes an airfoil having pressure and suction sides joined together at leading and trailing edges. The airfoil further includes a supply channel for receiving compressed air, and has an elongate recess disposed in at least one of the pressure and suction sides which is separated from the supply channel by a partition. The partition includes a plurality of spaced apart flow metering holes disposed in flow communication with the supply channel. A transpiration strip is fixedly joined to the airfoil in the recess and spaced from the partition to define a plenum for receiving the compressed air from the metering holes. The transpiration strip is pervious for channeling the compressed air from the plenum in a blanket of film cooling boundary layer air therefrom.

Turbine blade having transpiration strip cooling and method of

A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.

Chordally bifurcated turbine blade

This invention relates to a multiple ply assembly form that is especially adapted for use with a computer printer and which enables the user to simultaneously generate an original and at least two copies of an invoice and the customer's itinerary with the latter appearing on the upturned face of the bottom ply which folds to produce a ticket jacket having both a ticket pocket on the inside and a boarding pass-receiving slit on the outside.

Growing community of inventors

Ipswich, MA, United States of America

David M Kercher