Paul Hanrahan resumes & CV records
Resumes
Paul Hanrahan
Paul Hanrahan
Paul Hanrahan
Work:
Hanrahan Paul M
Attorney
Attorney
Paul R Hanrahan, 61Sedona, AZ
Paul Hanrahan Phones & Addresses
Sedona, AZ
85 Songbird Ln, Farmington, CT 06032 860-6762889
North Palm Beach, FL
West Deptford, NJ
Mentions for Paul R Hanrahan
Publications & IP owners
Us Patents
System And Method For Reducing Fuel Cell Power Plant Emissions
US Patent:
2011028, Nov 17, 2011
Filed:
Jan 15, 2009
Appl. No.:
13/144713
Inventors:
John L. Preston - Hebron CT, US
Peter F. Foley - Manchester CT, US
Paul R. Hanrahan - Farmington CT, US
Joshua D. Isom - South Windsor CT, US
Peter F. Foley - Manchester CT, US
Paul R. Hanrahan - Farmington CT, US
Joshua D. Isom - South Windsor CT, US
Assignee:
UTC POWER CORPORATION - South Windsor CT
International Classification:
H01M 8/06
US Classification:
429415
Abstract:
A system and method for operating fuel cell power plant includes enclosing fuel bearing components, such as fuel cell stack and reformer into a fuel compartment separate from motorized components in a motor compartment and consuming leaked fuel in the fuel compartment using a fuel bearing component such as cell stack and/or burner thereby reducing fuel emissions from the plant.
Fluidized Bed Contaminant Separator And Water-Control Loop For A Fuel Reactant Stream Of A Fuel Cell
US Patent:
2012003, Feb 9, 2012
Filed:
Apr 27, 2009
Appl. No.:
13/263148
Inventors:
Joshua D. Isom - South Windsor CT, US
Leslie L. Vandine - Manchester CT, US
Derek W. Hildreth - Manchester CT, US
John L. Preston - Hebron CT, US
Paul R. Hanrahan - Farmington CT, US
Reni Lynn - Vernon CT, US
Leslie L. Vandine - Manchester CT, US
Derek W. Hildreth - Manchester CT, US
John L. Preston - Hebron CT, US
Paul R. Hanrahan - Farmington CT, US
Reni Lynn - Vernon CT, US
International Classification:
H01M 8/06
H01M 8/04
H01M 8/04
US Classification:
429410
Abstract:
A fluidized contaminant separator and water-control loop () decontaminates a fuel reactant stream of a fuel cell (). Water passes over surfaces of an ammonia dissolving media () within a fluidized bed () while the fuel reactant stream simultaneously passes over the surfaces to dissolve contaminants from the fuel reactant stream into a separated contaminant and water stream. A fuel-control heat exchanger () upstream from the scrubber () removes heat from the fuel stream. A water-control loop () directs flow of the separated contaminants and water stream from an accumulator () through an ion exchange bed () which removes contaminants from the stream. Decontaminated water is directed back into the scrubber () to flow through the fluidized bed (). Separating contaminants from the fuel reactant stream and then isolating and concentrating the separated contaminants within the ion exchange material () minimizes costs and maintenance requirements.
Thermal Energy Recycling Fuel Cell Arrangement
US Patent:
2013026, Oct 10, 2013
Filed:
Jan 3, 2011
Appl. No.:
13/996081
Inventors:
Paul R. Hanrahan - Farmington CT, US
Assignee:
UTC POWER CORPORATION - South Windsor CT
International Classification:
H01M 8/04
US Classification:
429440
Abstract:
An example fuel cell arrangement includes a fuel cell stack configured to receive a supply fluid and to provide an exhaust fluid that has more thermal energy than the supply fluid. The arrangement also includes an ejector and a heat exchanger. The ejector is configured to direct at least some of the exhaust fluid into the supply fluid. The heat exchanger is configured to increase thermal energy in the supply fluid using at least some of the exhaust fluid that was not directed into the supply fluid.
Brush Seal Assembly
US Patent:
5066025, Nov 19, 1991
Filed:
Jun 18, 1990
Appl. No.:
7/539241
Inventors:
Paul R. Hanrahan - Farmington CT
International Classification:
F16J 1548
F16J 900
F16J 900
US Classification:
277 53
Abstract:
Support structure (12) includes a recess (32) which accepts short plate (20) of brush seal (10). The recess will not accept long plate (18) of the seal. Retaining ring groove (28) accepts the retaining ring (26) only if the seal is installed in the proper direction. Reverse installation is precluded without special machining of the brush seal.
Augmented Drive Of Compressors Via Differential And Multistage Turbine
US Patent:
2022034, Nov 3, 2022
Filed:
Jul 14, 2022
Appl. No.:
17/864982
Inventors:
- Farmington CT, US
Paul R. Hanrahan - Sedona AZ, US
Paul R. Hanrahan - Sedona AZ, US
Assignee:
RAYTHEON TECHNOLOGIES CORPORATION - Farmington CT
International Classification:
F02C 3/113
F02C 3/14
F02C 9/56
F02K 3/10
F02C 3/14
F02C 9/56
F02K 3/10
Abstract:
A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
Pressure Gain For Cooling Flow In Aircraft Engines
US Patent:
2022034, Oct 27, 2022
Filed:
Apr 23, 2021
Appl. No.:
17/238793
Inventors:
- Farmington CT, US
Paul R. Hanrahan - Sedona AZ, US
Paul R. Hanrahan - Sedona AZ, US
International Classification:
F01D 5/08
Abstract:
Gas turbine engines and rotor arms thereof are described. The gas turbine engines include a first disk, a second disk, and a rotor arm arranged between and connecting the first disk to the second disk, wherein a cavity is defined at least between the rotor arm and the first disk. The rotor arm includes a radial portion having an inner diameter end and an outer diameter end, an axial portion having a first end and a second end, wherein the first end of the axial portion is connected to the outer diameter end of the radial portion, at least one entrance flow path defined within the radial portion extending from the inner diameter end to the outer diameter end, and at least one exit aperture arranged proximate the second end of the axial portion.
Turbofan With Offset Gas Generator And Auxiliary Power Core
US Patent:
2023003, Feb 9, 2023
Filed:
Aug 4, 2021
Appl. No.:
17/393508
Inventors:
- Farmington CT, US
Paul R. Hanrahan - Sedona AZ, US
Christopher J. Hanlon - Sturbridge MA, US
Paul R. Hanrahan - Sedona AZ, US
Christopher J. Hanlon - Sturbridge MA, US
International Classification:
F02C 3/10
F02C 7/36
F02C 6/02
F01D 13/00
F02C 7/36
F02C 6/02
F01D 13/00
Abstract:
A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.
Low Profile Rotating Bearing Centering Spring
US Patent:
2021040, Dec 30, 2021
Filed:
Jun 26, 2020
Appl. No.:
16/913019
Inventors:
- Farmington CT, US
Paul R. Hanrahan - Farmington CT, US
Paul R. Hanrahan - Farmington CT, US
International Classification:
F04D 29/059
F16C 19/36
F16C 33/58
F16C 35/073
F16C 19/36
F16C 33/58
F16C 35/073
Abstract:
A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.
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