Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Masoud Roshan Fekr

Rana Foroutan

Panagiota Tsifourdaris

Othmane Leghzaouni

Robert Huszar

Stephane Bigras

Daniel Lecuyer

Vincent Paradis

Lorenzo Sanzari

Francis Gemme

Marc-Antoine Mailloux-Labrousse

Abdulhalim Twahir

Fariba Ajalli

William Mindenhall

A rotor blade includes an airfoil, a root, a cooling air passage and a cooling air deflector. The root extends axially along an axis between a first end of the root and a second end of the root. The root extends laterally between a first side of the root and a second side of the root. The root projects radially inward and away from the airfoil to an inner end of the root. The cooling air passage includes a passage inlet disposed at the inner end. The cooling air passage projects radially into the rotor blade from the passage inlet. The cooling air deflector projects radially inward from the inner end of the root to an inner end of the cooling air deflector. The cooling air deflector is disposed at the second side and is spaced laterally from the first side. The cooling air deflector includes a cooling air aperture.

Rotor blade with apertured cooling air deflector

A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having a first inner opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the first inner opening extends from and is located within two second inner openings, one of which extends from the leading edge of the root portion and the other extends from the trailing edge of the root portion.

Test blade for gas turbine engine and method of making

A containment case includes an annular body bound by an inner surface and an outer surface and an outer surface feature extending outward from the outer surface and an inner surface feature extending inwards from the inner surface. The annular body includes a containment section and an inner reinforcement section radially inward from the inner surface subtending a sector of the containment section. The reinforcement section includes a reinforcement thickness that is greater than a casing thickness of the containment section at least partially coinciding with the outer surface feature.

Containment engine case with local features and inner surface reinforcement section

A containment case includes an annular body bound by an inner surface and an outer surface and an outer surface feature extending outward from the outer surface. The annular body includes a containment section and an outer reinforcement section extending outwards from the outer surface and subtending a sector of the containment section. The reinforcement section includes a reinforcement thickness that is greater than a casing thickness of the containment section at least partially coinciding with the outer surface feature.

Containment engine case with local features and outer surface reinforcement section

A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.

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 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 exterior 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 described 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.

A turbine blade for a gas turbine engine, the turbine blade having a peripheral blade tip wall surrounding a radially recessed tip pocket, the peripheral blade tip wall having: a wall height; a leading edge; a trailing edge; a pressure side wall; and a suction side wall; and a rib extending between the pressure side wall and the suction side wall defining a leading portion and a trailing portion of the radially recessed tip pocket, the rib having a rib height less than the wall height.

Growing community of inventors

Saint-Lambert, Canada

Masoud Roshan Fekr