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Matthew J Forcier

from Groton, NY
Age ~49
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Also known as:
Matthew E Forcier, Mathew E Forcier, Matt E Forcier, Forcier E Matthew
Related to:
Zach Forcier
Connected to:
Aimee L Forcier, 47Amy K Forcier, 53Cara R Forcier, 45Cindy L Forcier, 64Debra N Forcier, 70Helene F Forcier, 78Holly V Forcier, 56Jeannine E Forcier, 63Kathleen A Forcier, 74Lisa P Forcier, 76

Matthew Forcier Phones & Addresses

  • Groton, NY
  • 415 S Titus Ave #C205, Ithaca, NY 14850 (607) 229-0222
  • Ithaca College, NY
  • 11 Washington St, Rocky Hill, CT 06067 (860) 257-0679
  • 30 Glastonbury Ave, Rocky Hill, CT 06067 (860) 257-0679
  • 819 Scarlett Dr, Towson, MD 21286
  • Baltimore, MD
  • Glastonbury, CT
  • Schenectady, NY

Publications

Us Patents

Tandem Blade Rotor Disk

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US Patent:
20230116394, Apr 13, 2023
Filed:
Dec 7, 2022
Appl. No.:
18/077084
Inventors:
- Farmington CT, US
MATTHEW P. FORCIER - South Windsor CT, US
Assignee:
RAYTHEON TECHNOLOGIES CORPORATION - Farmington CT
International Classification:
F04D 29/32
F01D 5/34
F01D 5/14
F01D 5/30
F04D 29/64
F04D 19/02
Abstract:
A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.

Tandem Blade Rotor Disk

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US Patent:
20200392967, Dec 17, 2020
Filed:
May 4, 2020
Appl. No.:
16/866303
Inventors:
- Farmington CT, US
MATTHEW P. FORCIER - South Windsor CT, US
Assignee:
RAYTHEON TECHNOLOGIES CORPORATION - Farmington CT
International Classification:
F04D 29/32
F01D 5/34
F01D 5/14
F01D 5/30
F04D 29/64
F04D 19/02
Abstract:
A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

Tandem Blade Rotor Disk

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US Patent:
20190010956, Jan 10, 2019
Filed:
Jul 6, 2017
Appl. No.:
15/642677
Inventors:
- Farmington CT, US
MATTHEW P. FORCIER - South Windsor CT, US
Assignee:
UNITED TECHNOLOGIES CORPORATION - Farmington CT
International Classification:
F04D 29/32
F04D 19/02
Abstract:
A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

Actively-Driven Bleed Source Switching

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US Patent:
20180334918, Nov 22, 2018
Filed:
May 22, 2017
Appl. No.:
15/601544
Inventors:
- Farmington CT, US
William K. Ackermann - East Hartford CT, US
Matthew P. Forcier - South Windsor CT, US
International Classification:
F01D 17/10
F01D 17/14
F01D 5/02
F04D 27/00
F01D 21/00
F01D 25/12
Abstract:
A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, and a bleed duct in fluid communication with the bleed ports and configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet. A valve is located at each bleed port of and is configured to move between an opened position and a closed position, and one or more sensors are located along the bleed flowpath to sense one or more conditions of the bleed air cooling system. The valve at a particular bleed port is moved to the opened position based on the sensed one or more conditions.

Active Bleed Flow Modulation

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US Patent:
20180334962, Nov 22, 2018
Filed:
May 22, 2017
Appl. No.:
15/601499
Inventors:
- Farmington CT, US
William K. Ackermann - East Hartford CT, US
Matthew P. Forcier - South Windsor CT, US
International Classification:
F02C 7/18
Abstract:
A bleed air cooling system for a gas turbine engine includes a bleed port located at an axial location of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. A modulating valve is located at the bleed duct and is movable between a fully open position and a fully closed position to regulate the bleed airflow through the bleed duct based on one or more operating conditions of the gas turbine engine.

Bleed Flow Safety System

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US Patent:
20180334965, Nov 22, 2018
Filed:
May 22, 2017
Appl. No.:
15/601524
Inventors:
- Farmington CT, US
Matthew P. Forcier - South Windsor CT, US
William K. Ackermann - East Hartford CT, US
International Classification:
F02C 9/18
F01D 17/02
F01D 9/06
F02C 7/18
Abstract:
A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.

Passively-Driven Bleed Source Switching

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US Patent:
20180334966, Nov 22, 2018
Filed:
May 22, 2017
Appl. No.:
15/601563
Inventors:
- Farmington CT, US
William K. Ackermann - East Hartford CT, US
Matthew P. Forcier - South Windsor CT, US
International Classification:
F02C 9/18
F02C 7/18
F01D 9/06
Abstract:
A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

High Temperature Disk Conditioning System

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US Patent:
20180258862, Sep 13, 2018
Filed:
May 15, 2018
Appl. No.:
15/979906
Inventors:
- Farmington CT, US
Matthew P. Forcier - South Windsor CT, US
Assignee:
United Technologies Corporation - Farmington CT
International Classification:
F02C 9/18
F01D 5/08
F01D 9/06
F01D 11/24
F01D 25/10
F02C 3/34
F02C 7/12
Abstract:
A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.
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Matthew J Forcier from Groton, NY, age ~49 Get Report