Pratt-whitney Canada Corp

Jasrobin Grewal

Philippe Boyer

Michael Papple

Panagiota Tsifourdaris

Vincent Paradis

Domenico Di Florio

Othmane Leghzaouni

Robert Huszar

Prakul Mittal

Yashiva Dorsamy

Sami Girgis

Eduardo David Hawie

Remo Marini

Daniel Lecuyer

Franco Di Paola

Mohammed Ennacer

Krishan Mohan

Nicolas Grivas

Niloofar Moradi

Gaetan Girard

Constantinos Ravanis

Marc-Antoine Mailloux-Labrousse

Jonathan Dorai

Dan Olaru

Jonathan Tebeka

An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The rotor blades are arranged circumferentially around the rotor disk in an array. The array of the rotor blades are divided into a plurality of sectors including a first sector and a second sector. The rotor blades are disposed in the first sector including a plurality of first rotor blades. Each of the first rotor blades includes a first coating. The rotor blades are disposed in the second sector including a plurality of second rotor blades. Each of the second rotor blades includes a second coating that is different from the first coating.

Tailoring rotor blade coating to tune gas turbine engine bladed rotor

An assembly is provided for a gas turbine engine. This assembly includes an integrally bladed rotor and a damper. The integrally bladed rotor is rotatable about an axis. The integrally bladed rotor includes a plurality of rotor blades and a rotor disk. The rotor blades are arranged circumferentially around and project radially out from the rotor disk. The rotor disk includes a flange, a groove and a plurality of slots. The groove extends circumferentially around the axis within the flange. The groove projects radially into the flange from an inner side of the flange. The slots are arranged circumferentially about the axis along the groove. Each of the slots projects radially into the flange from the inner side of the flange. The damper is mounted to the rotor disk and seated within the groove.

Damped bladed rotor for gas turbine engine

A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Turbine blade airfoil profile

A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

High pressure turbine blade airfoil profile

There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.

Vane segment with ribs

A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Compressor turbine blade airfoil profile

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Pincourt, Canada

Jasrobin Grewal