Justin M Urban

age ~46

from Charleston, SC

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Apparatus And Method For Preventing Inlet Vortex
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US Patent:

20030217593, Nov 27, 2003
Filed:

May 22, 2002
Appl. No.:

10/063900
Inventors:

Terry Clark - East Hartford CT, US
Justin Urban - Tolland CT, US
International Classification:

G01L003/26
US Classification:

073/116000
Abstract:

A method of operating a gas turbine engine for testing, comprising: providing an aircraft on a tarmac, the aircraft having a gas turbine engine with an inlet; selecting a power setting for the engine that is capable of producing a vortex between the inlet and the tarmac; and inhibiting formation of the vortex. A suppressor for preventing a vortex between an inlet of a gas turbine engine on an aircraft and a tarmac. The suppressor comprises: a base facing the tarmac; and an inclined surface extending in a direction from the tarmac towards the inlet at an angle to the base. The suppressor prevents formation of the vortex.

Gas Turbine Engine With Bleed Duct For Minimum Reduction Of Bleed Flow And Minimum Rejection Of Hail During Hail Ingestion Events
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US Patent:

20120070271, Mar 22, 2012
Filed:

Sep 21, 2010
Appl. No.:

12/886807
Inventors:

Justin R. Urban - Tolland CT, US
Anthony R. Bifulco - Ellington CT, US
International Classification:

F01D 17/00
US Classification:

415145
Abstract:

A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Metal-Based Fuel And Fuel Delivery Systems
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US Patent:

20230008152, Jan 12, 2023
Filed:

Apr 25, 2022
Appl. No.:

17/728510
Inventors:

- Farmington CT, US
JUSTIN R. URBAN - Tolland CT, US
Assignee:

RAYTHEON TECHNOLOGIES CORPORATION - Farmington CT
International Classification:

F02C 3/26
F02C 6/00
Abstract:

A system for generating combustion gases in a turbine engine may comprise a combustion chamber and a fuel injection system configured to inject a metal-based fuel into the combustion chamber. A metal-based fuel source may be configured to deliver the metal-based fuel to the fuel injection system. The metal-based fuel may comprise a metal powder.

System And Method For Analyzing Engine Test Data In Real Time
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US Patent:

20200400531, Dec 24, 2020
Filed:

Jun 21, 2019
Appl. No.:

16/448365
Inventors:

- Farmington CT, US
Justin R. Urban - Tolland CT, US
Michael J. Giering - Bolton CT, US
Quan Long - West Hartford CT, US
Alexandria Dorgan - West Hartford CT, US
International Classification:

G01M 15/14
F02D 35/02
B64F 5/60
Abstract:

A system for providing real time aircraft engine sensor analysis includes a computer system configured to receive an engine operation data set in real time. The computer system includes a machine learning based analysis tool and a user interface configured to display a real time analysis of the engine operation data set. The user interface includes at least one portion configured to identify a plurality of anomalies in the engine operation data set.

Gas Turbine Engine With Heat Pipe System
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US Patent:

20180209342, Jul 26, 2018
Filed:

Jan 23, 2017
Appl. No.:

15/412203
Inventors:

- Farmington CT, US
Gabriel L. Suciu - Glastonbury CT, US
Justin R. Urban - Tolland CT, US
International Classification:

F02C 7/12
F02C 3/04
F28D 15/02
F28D 15/04
Abstract:

A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.

Nacelle Deflection Measurement Assembly
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US Patent:

20170292882, Oct 12, 2017
Filed:

Apr 11, 2016
Appl. No.:

15/095199
Inventors:

- Farmington CT, US
Michael Joseph Murphy - Windsor CT, US
Justin R. Urban - Tolland CT, US
Robert E. Malecki - Storrs CT, US
William W. Rice - South Glastonbury CT, US
David W. Lamarre - Colchester CT, US
International Classification:

G01L 5/13
B64D 27/10
G01M 15/14
B64C 7/02
Abstract:

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

Monitoring A Dynamic Parameter Such As Torque In A Rotational System
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US Patent:

20160281528, Sep 29, 2016
Filed:

Nov 11, 2014
Appl. No.:

15/033828
Inventors:

- Hartford CT, US
Justin R. Urban - Tolland CT, US
International Classification:

F01D 21/00
F01D 15/12
F01D 5/12
F01D 5/02
F01D 25/24
Abstract:

A system is provided for a turbine engine. The system includes a rotor assembly and a monitoring system. The rotor assembly includes a plurality of rotor blades connected to a shaft. The monitoring system includes a processing system. This processing system is adapted to receive blade data indicative of a rotational position of at least a first of the rotor blades. The processing system is also adapted to process shaft data with the blade data to provide torque data indicative of a torque to which at least a portion of the rotor assembly is being subjected, where the shaft data is indicative of a rotational position of the shaft.