Benjamin E Toby, Age 594 Hundred Acres Rd, Newtown, CT 06470
Benjamin Toby Phones & Addresses
Newtown, CT
3445 Rosemary Ave, Glendale, CA 91208 (818) 541-1776
69 Alberts Hill Rd, Sandy Hook, CT 06482 (203) 426-4550
New Canaan, CT
Sierra Madre, CA
Danbury, CT
San Francisco, CA
Laguna Beach, CA
West Orange, NJ
San Clemente, CA
Mentions for Benjamin E Toby
Publications & IP owners
Us Patents
Gas Turbine Engine Having A Multi-Stage Multi-Plane Combustion System
US Patent:
6684642, Feb 3, 2004
Filed:
Jun 17, 2002
Appl. No.:
10/171684
Inventors:
Jeffrey W. Willis - Lexington KY
Guillermo Pont - Los Angeles CA
Benjamin E. Toby - Sierra Madre CA
Guillermo Pont - Los Angeles CA
Benjamin E. Toby - Sierra Madre CA
Assignee:
Capstone Turbine Corporation - Chatsworth CA
International Classification:
F02C 300
US Classification:
60746, 60737
Abstract:
A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
Multi-Stage Multi-Plane Combustion Method For A Gas Turbine Engine
US Patent:
2002014, Oct 17, 2002
Filed:
Jun 17, 2002
Appl. No.:
10/171676
Inventors:
Jeffrey Willis - Lexington KY, US
Guillermo Pont - Los Angeles CA, US
Benjamin Toby - Sierra Madre CA, US
Robert McKeirnan - Westlake Village CA, US
Guillermo Pont - Los Angeles CA, US
Benjamin Toby - Sierra Madre CA, US
Robert McKeirnan - Westlake Village CA, US
International Classification:
F02C007/22
US Classification:
060/804000, 060/746000
Abstract:
A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
Multi-Stage Multi-Plane Combustion Method For A Gas Turbine Engine
US Patent:
2004014, Jul 29, 2004
Filed:
Dec 12, 2003
Appl. No.:
10/733271
Inventors:
Jeffrey Willis - Lexington KY, US
Guillermo Pont - Los Angeles CA, US
Benjamin Toby - Sierra Madre CA, US
Robert McKeirnan - Westlake Village CA, US
Guillermo Pont - Los Angeles CA, US
Benjamin Toby - Sierra Madre CA, US
Robert McKeirnan - Westlake Village CA, US
International Classification:
F02C007/22
US Classification:
060/776000, 060/737000, 060/746000
Abstract:
A low emissions combustion method wherein, in an embodiment, a plurality of tangential fuel injectors introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
Multi-Stage Multi-Plane Combustion System For A Gas Turbine Engine
US Patent:
6453658, Sep 24, 2002
Filed:
Feb 24, 2000
Appl. No.:
09/512986
Inventors:
Jeffery W. Willis - Lexington KY
Guillermo Pont - Los Angeles CA
Benjamin E. Toby - Sierra Madre CA
Guillermo Pont - Los Angeles CA
Benjamin E. Toby - Sierra Madre CA
Assignee:
Capstone Turbine Corporation - Chatsworth CA
International Classification:
F02C 300
US Classification:
60 3936, 60746
Abstract:
A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
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