David J Candelori, 63458 Weir St LOT 12NBS, Glastonbury, CT 06033

2011013, Jun 9, 2011

Dec 4, 2009

12/631082

Bryan P. Dube - Columbia CT, US
Edward F. Pietraszkiewicz - Southington CT, US
David J. Candelori - Glastonbury CT, US

United Technologies Corporation - Hartford CT

F01D 25/12
B22C 9/10
B22C 7/00
F01D 5/18
G06F 19/00
B26F 1/00

415115, 249175, 164235, 164 45, 428586, 700146, 83 30, 416 97 R

If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a shear zone and a fracture zone. The shear zone of the RMC will cast a relatively narrow portion of the post near one end; whereas the fracture zone will cast a relatively broader portion near the other end. The broader portion will also have a relatively shallow transition to the adjacent face of the slot-like passageway cast by the RMC. Where there is a stress asymmetry in the cast article in-use, the punching direction may be chosen so that the relatively broad portions of the post fall along the relatively higher stress face of the passageway.

4869640, Sep 26, 1989

Sep 16, 1988

7/245250

Frederick M. Schwarz - Glastonbury CT
David J. Candelori - Glastonbury CT

United Technologies Corporation - Hartford CT

F04D 2958

415115

A temperature controlled rotating seal (46) includes an annular runner (48) having knife edges (50) and a surrounding static shroud (44). Baffles (64, 66) extend radially from the adjacent rotor (10) and a static stator vane assembly (36), forming a plurality of annular mixing volumes (60, 62) disposed upstream of the seal (46). Cool air (70) is provided to the innermost mixing volume (62) thereby controlling the local gas temperatures at the rotor periphery (14).

5224332, Jul 6, 1993

Apr 17, 1992

7/870069

Frederick M. Schwarz - Glastonbury CT
David J. Candelori - Glastonbury CT
Richard D. Brooke - Manchester CT

F02G 300

60 3902

Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area at high sensed speeds. Valve and thermocouples are checked for proper operation. Immediate alerts and maintenance messages are established along with fail safe operating conditions upon fault detection. Over cooling of the seal area during low power operation, in anticipation of a power increase, is used to improve low cycle fatigue life of the turbine disk and seal runner.

5157914, Oct 27, 1992

Dec 27, 1990

7/634905

Frederick M. Schwarz - Glastonbury CT
David J. Candelori - Glastonbury CT
Richard D. Brooke - Manchester CT

United Technologies Corporation - Hartford CT

F01D 514

60 3929

Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane surface from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area. A thermocouple is located in a bypass around a portion of the seal, being radially installed through a hollow vane and an opening in the seal shroud.

5857837, Jan 12, 1999

Jun 26, 1997

8/883522

Mark F. Zelesky - Coventry CT
Dominic J. Mongillo - New Britain CT
David J. Candelori - Glastonbury CT
Gary D. Steuber - Loveland OH

United Technologies Corporation - Hartford CT

F01D 518

416 97R

A coolable airfoil (25) for a gas turbine engine includes a leading edge portion (52) cooled by a combination of radial and impingement flows through internal passages (80) and (90) separated by an internal wall (95) which is imperforate along a radially inner portion (100) thereof and apertured along a radially outer portion (105) thereof.

2017033, Nov 23, 2017

May 23, 2016

15/161742

- Farmington CT, US
David J. Candelori - Glastonbury CT, US

F01D 25/32
F01D 21/00
F02C 3/04
F01D 5/18
F01D 25/12
F01D 9/04

A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

2016017, Jun 23, 2016

Mar 5, 2015

14/639507

- Hartford CT, US
Gaurav M. Patel - Glastonbury CT, US
Jeffery Scott Hembree - Ellington CT, US
San Quach - East Hartford CT, US
Mark F. Zelesky - Bolton CT, US
David J. Candelori - Glastonbury CT, US
Dominic J. Mongillo - West Hartford CT, US

F01D 5/18
F01D 5/28
F01D 11/08
F01D 5/14
F01D 9/04

A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating. The component is then coated. A component and an intermediate component for use in a gas turbine engine are also disclosed.

2016017, Jun 23, 2016

Sep 23, 2015

14/862422

- Hartford CT, US
Christopher King - Bristol CT, US
Steven Bruce Gautschi - Naugatuck CT, US
David J. Candelori - Glastonbury CT, US

United Technologies Corporation - Hartford CT

F01D 5/18

The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.