Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Allison Advanced Development Company

Tab Michael Heffernan

Douglas David Dierksmeier

Jeffrey F Rhodes

Okey Kwon

Michel Shawn Smallwood

Peter C Vandervaart

Kenneth M Pesyna

Matthew T Kush

Brett J Barker

James Christopher Muskat

Randolph Clifford Helmink

Jack D Petty, Sr

Mohan Razdan

Mark Steven McCormick

Michael S Bell

Peter L Vandervaart

A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures.

Dual-wall impingement, convection, effusion combustor tile

A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis.

Turbine wheels with preloaded blade attachment

An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.

Turbine endwall and tip cooling for dual wall airfoils

A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.

Gas turbine engine component arrangement

A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.

Cooled gas turbine engine component

A method includes removing a casting shell and core from a cast component, which may be a gas turbine blade. The method further includes utilizing a focused removal technique, such as a water jet or laser drill, to remove a portion of a virtual pattern cast (VPC) shell from the cast component. The cast component is then exposed to a leaching solution and high pressure water wash to remove an internal core material and a portion of the VPC shell remainder from the cast component. The method further includes exposing the cast component to a high agitation leaching solution and to the high pressure water wash for a minimal time. An electroless nickel-boron coating is then applied to the cast component, and an electrolytic palladium coating is further applied to the cast component. The cast component is further exposed to a high agitation leaching solution for an extended period.

System, method, and apparatus for leaching cast components

A gas turbine engine airfoil including at least one outer tile coupled to a supporting member. The outer tile is coupled to the supporting member by a pin passing though the supporting member and the outer tile.

Gas turbine engine airfoil

An active blade clearance control system for a gas turbine engine. The clearance between the tip of a rotatable blade and an inner surface of a blade track is adjusted by moving the blade track relative to the tip of the blades. A split control ring is manipulated to adjust tension therein and a resulting force is transmitted to an inner member. The plurality of blade tracks are coupled to the inner member and move in response to the force transmitted from the split control ring.

Apparatus and method for active control of blade tip clearance

The clearances between an array of turbine blades and its surrounding blade track may be controlled by an expansion control material system supporting the blade tracks. The blade track support hoop is placed in tension by the expansion control material placed therein and the expansion control material is placed in compression.

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Plainfield, IN, United States of America

Tab Michael Heffernan