An array of rotor blades is provided. The array includes a rotor disk (22) defming a plurality of slots (23). A first rotor blade (24) that includes a first platform (34) between a first airfoil (28) and a first shank portion (32) is coupled with a first slot (23) of the rotor disk (22) via the first shank portion (32). The first rotor blade (24) further includes a pair of oppositely disposed flanges (36) positioned between the first platform (34) and the first shank portion (32) and extending beyond a longitudinal side edge (39) defined by the first platform (34). A second rotor blade, that includes a second platform (38) defming a pair of oppositely disposed overhang lips (40) and positioned between a second airfoil and a second shank portion (32), is coupled with a second slot (23) of the rotor disk (22) via the second shank portion (32). The second rotor blade is positioned adjacent to the first rotor blade such that one of the overhang lips (40) of the second platform (38) is positioned over one of the flanges (36) of the first rotor blade. Methods are also generally provided for installing rotor blades onto a rotor disk (22).

Coupled blade platforms and methods of sealing

An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.

Integrated strut and turbine vane nozzle arrangement

A turbine case cooling system including a turbine assembly having an inlet and an outlet and surrounded by a turbine casing. The turbine case cooling system is arranged to selectively impingement cool at least part of the turbine casing. The system includes an annular structure that is radially spaced from the turbine casing and includes a downstream end. The system includes an annular duct that is spaced radially outwardly from the turbine casing and radially inwardly from the annular structure. The duct is sealingly coupled to the turbine casing at a first end towards the turbine inlet, and a second end extends axially towards the downstream end of the annular structure and the turbine outlet.

Turbine case cooling system

A disclosed stator vane assembly includes a plurality of stator vane elements supported within a case about an axis. Each of the plurality of stator vane elements includes a platform having a recess on a first side and a tongue on a second side. The tongue overlaps a recess of an adjacent one of the plurality of stator vane elements with at least one of the recess and the tongue includes a crowned surface forming a seal.

Shiplap cantilevered stator

A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides, providing cold side details separately from the base sheet, and mounting the cold side details to the cold facing side of the base sheet. The cold side details may be brazed to the base sheet.

Fabricated heat shield

A stator vane segment, for constructing a circumferential array of like segments in a gas turbine engine, each segment in the array being separated by an axially extending joint from an adjacent segment and being releasably mounted to an outer engine casing. Each stator vane segment has: a number of vane airfoils spanning radially between an inner platform and an outer platform, and the outer platform includes: a casing mounting fastener on an outer surface and mating lateral joint edges extending between forward and aft edges.

Hp segment vanes

A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.

Active turbine or compressor tip clearance control

A gas turbine engine includes an annular plenum (52) defined with an outer skin (54) and a perforated inner skin (56) for receiving selective air flow to impinge a support case (40) which supports shrouds (34,38) of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. A bobbin-type transfer tube (62) for supplying cooling air into the plenum (52), is provided between an outer case (13) of the engine and the plenum (52) such that the thermally induced relative movement of the outer case (13) and the plenum (52) is permitted.

Gas turbine engine with an active tip clearance control

A method for centering an engine structure such as a bearing housing is provided which may be used for example, during assembly of a mid turbine frame or other engine case structure. The method according to one embodiment may include machining spokes with an outer case of the mid turbine frame in situ to eliminate stack-up and then applying the retaining device to retain the spokes with respect to the outer case, thereby assuring the co-axial relationship between the outer case and the bearing housing supported within the mid turbine frame.

Engine structure assembly procedure

The method for forming a turbofan mixer comprises providing a single monolithic and generally flat annular sheet metal blank, providing a die surface substantially corresponding in shape to a turbofan mixer shape, positioning the blank with reference to the die surface, and forcing the blank against the die surface to transform the blank into a monolithic turbofan mixer.

Danny Mills

Papers

Hp segment vanes

Active turbine or compressor tip clearance control

Gas turbine engine with an active tip clearance control

Engine structure assembly procedure

Method and apparatus for forming a turbofan mixer