United Technologies Corporation

Raytheon Technologies Corporation

Jonathan J Earl

Mark John Rogers

Carl S Richardson

Richard K Hayford

Mark David Ring

Eric A Kuehne

Kenneth E Carman

Charles H Warner

Dominic J Mongillo, Jr

Paul M Lutjen

Eric A Hudson

Susan M Tholen

James N Knapp

Matthew R Willett

Virginia L Ross

Gerald D Cassella

Neil L Tatman

Scot Adams Webb

Nicholas R Leslie

Christopher B Lyons

Randall J Butcher

Scot A Webb

David Cassella

Matthew M Zietala

A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

Vane seal system and seal therefor

A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to the second end-of-cluster vane at an interface that includes an angled load interface therebetween; and a multiple of base vanes between the first end-of-cluster vane and the neighbor vane, the angled load interface different than an interface between each of the multiple of base vane.

Stator assembly for a gas turbine engine

A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.

Blade outer air seal cooling scheme

An assembly includes a first vane pack, a second vane pack, and a liner lock segment. The first vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack is disposed to abut the first vane pack. The liner lock segment is disposed between the first vane pack and the second vane pack.

Liner lock segment

A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.

Vane seal system having spring positively locating seal member in axial direction

One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another.

Stator segment

A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.

Split damped outer shroud for gas turbine engine stator arrays

Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs.

Systems and methods for anti-rotational features

A vane cluster for a gas turbine engine includes multiple singlet vanes and a forward wear liner connecting a forward edge of each singlet vane, thereby allowing the vane cluster to be manipulated as a single component.

Singlet vane cluster assembly

An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360&#xb0; in length.

Liner and method of assembly

A stator assembly for a turbofan gas turbine engine is disclosed. The stator assembly is coupled to a shroud of the engine. The stator assembly includes an endless case fixedly coupled to the engine shroud. The case includes a forward portion, an aft portion and a central portion disposed therebetween. The case extends about an axis of the engine. The forward and aft portions of the case include rails that extend towards each other and form forward and aft pockets with the central portion respectfully. The stator assembly also includes a locking stator segment. The locking stator segment includes a shroud that includes a forward hook and a pair of aft hooks with a platform disposed therebetween. The forward and aft hooks are retained in the forward and aft pockets of the case respectfully.

Growing community of inventors

Wells, ME, United States of America

Jonathan J Earl