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Eric John Wehmeier

from West Hartford, CT
Age ~58
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Also known as:
Eric J Wehmeier, Eric Wehmeir
Phone and address:
71 Sylvan Ave, Hartford, CT 06107
(860) 561-2385
Related to:
Holly Ann Wehmeier, 60Mary Lou Wehmeier, 85
Connected to:
Sandra J Wehmeier, 79Annette A Wehmeyer, 72Margaret M Wehmeyer, 99Paula C Wehmeyer, 69Robin Wehmeyer, 60Robert E Wehmueller, 77Arthur L Wehner, 80Brett L Wehner, 56Courtney R Wehner, 36Edwin P Wehner, 81

Eric Wehmeier Phones & Addresses

  • 71 Sylvan Ave, West Hartford, CT 06107 (860) 561-2385
  • 103 Loomis St, West Hartford, CT 06107 (860) 561-2385
  • Hartford, CT
  • Kirkland, WA
  • Bellevue, WA
  • Millstadt, IL
  • Mukilteo, WA

Public records

Vehicle Records

Eric Wehmeier

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Address:
71 Sylvan Ave, West Hartford, CT 06107
Phone:
(860) 561-2385
VIN:
1G1ZC5E11BF195998
Make:
CHEVROLET
Model:
MALIBU
Year:
2011

Publications

Us Patents

Gas Turbine Engine With Variable Area Fan Nozzle Positioned For Starting

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US Patent:
8291690, Oct 23, 2012
Filed:
Feb 7, 2012
Appl. No.:
13/367579
Inventors:
Eric J. Wehmeier - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 3/02
US Classification:
602263, 60771, 602261, 60778, 60786
Abstract:
A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful when the gas turbine engine is being restarted while an associated aircraft is in the air, and is relied upon to increase windmill speed of the compressor and turbine rotors. A method and nozzle are also disclosed.

Gas Turbine Engine With Variable Area Fan Nozzle Positioned For Starting

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US Patent:
8596072, Dec 3, 2013
Filed:
Sep 14, 2012
Appl. No.:
13/617506
Inventors:
Eric J. Wehmeier - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 3/02
US Classification:
60771, 602263, 602261, 60786
Abstract:
A gas turbine engine has a compressor section, a low spool, and a fan. The fan delivers air into the compressor section and into a bypass duct having a variable area nozzle. The compressor section compresses air and delivers it into a combustion section. The combustion section mixes air with fuel, igniting the fuel, and driving the products of the combustion across a turbine. The turbine drives the low spool. A control for the gas turbine engine is programmed to position the nozzle at startup of the engine to increase airflow across the fan. A variable inlet guide vane is positioned upstream of the compressor section. The control also positions the variable inlet guide vane at start-up to increase air flow across the compressor section.

Gas Turbine Engine With Compressor Inlet Guide Vane Positioned For Starting

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US Patent:
20130192195, Aug 1, 2013
Filed:
Feb 7, 2012
Appl. No.:
13/367742
Inventors:
Eric J. Wehmeier - West Hartford CT, US
International Classification:
F02K 3/02
US Classification:
60204, 602263
Abstract:
A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful when the gas turbine engine is being restarted while an associated aircraft is in the air, and is relied upon to increase windmill speed of the compressor and turbine rotors. A method and variable inlet vane are also disclosed.

Gas Turbine Engine With Compressor Inlet Guide Vane Positioned For Starting

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US Patent:
20140223916, Aug 14, 2014
Filed:
Apr 23, 2014
Appl. No.:
14/259180
Inventors:
- Hartford CT, US
Eric J. Wehmeier - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 3/13
US Classification:
60772, 60 3923
Abstract:
A gas turbine engine includes a compressor section, the compressor section including a variable inlet guide vane which is movable between distinct angles to control the airflow approaching the compressor section. A control is programmed to position the vane at startup of the engine to direct airflow across the compressor section. The engine includes a fan for delivering bypass air into a bypass duct positioned outwardly of a core engine including the compressor section. The position of the vane is configured to direct airflow across the compressor section while an aircraft associated with the gas turbine engine is in the air, and to increase a windmilling speed of the compressor section and the turbine rotors. A method and variable inlet vane are also disclosed.
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Eric John Wehmeier from West Hartford, CT, age ~58 Get Report