Brian J Schuler

US Patent:

20160369816, Dec 22, 2016

Filed:

Aug 31, 2016

Appl. No.:

15/252331

Inventors:

- Farmington CT, US
Matthew P. Forcier - South Windsor CT, US
Brian J. Schuler - West Hartford CT, US

International Classification:

F04D 29/58
F04D 29/54
F04D 29/32

Abstract:

A gas turbine engine has a compressor section with a downstream most blade stage and a downstream vane row positioned downstream of the downstream most blade stage. The downstream most blade stage includes a plurality of blade pairs with the majority of blade pairs being circumferentially spaced apart from others of the blade pairs, each the blade pair being operatively connected to a rotor disk disposed radially inward from the blade pairs with each blade pair including a forward blade and an aft blade. The aft blades are configured to further condition airflow with respect to the forward blade. A tangential onboard injector (TOBI) is positioned radially inwardly of the downstream vane row.

US Patent:

20160230559, Aug 11, 2016

Filed:

Feb 10, 2015

Appl. No.:

14/618041

Inventors:

- Hartford CT, US
Brian J. Schuler - West Hartford CT, US
Jordan T. Wall - Hartford CT, US

International Classification:

F01D 5/02
F01D 25/24
F01D 11/00
F01D 9/04

Abstract:

A rotor includes a rotor hub that is rotatable about an axis. The rotor hub includes a bore portion and a rim. An arm extends axially and radially inwardly from the rim. The arm has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side.

US Patent:

20160230575, Aug 11, 2016

Filed:

Feb 10, 2015

Appl. No.:

14/618035

Inventors:

- Hartford CT, US
Brian J. Schuler - West Hartford CT, US
Jordan T. Wall - Hartford CT, US

International Classification:

F01D 9/04
F01D 25/24
F01D 5/02

Abstract:

An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.

US Patent:

20160108735, Apr 21, 2016

Filed:

Oct 14, 2015

Appl. No.:

14/882722

Inventors:

- Farmington CT, US
Brian J. Schuler - West Hartford CT, US

International Classification:

F01D 5/14
F01D 9/04
F01D 11/00
F04D 19/02

Abstract:

A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages defined radially inward relative to the compressor case. The plurality of stages includes at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.

US Patent:

20150218955, Aug 6, 2015

Filed:

Mar 14, 2013

Appl. No.:

14/422368

Inventors:

- Hartford CT, US
Peter T. Schutte - Manchester CT, US
Brian J. Schuler - West Hartford CT, US
Anthony R. Bifulco - Ellington CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 5/28
F01D 5/14

Abstract:

A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.