William K Ackermann from 15 Butternut Dr, Hartford, CT 06118, age 63, Phone: 8605686394

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Secondary Flow Arrangement For Slotted Rotor
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US Patent:

20130108413, May 2, 2013
Filed:

Apr 30, 2012
Appl. No.:

13/459474
Inventors:

Gabriel L. Suciu - Glastonbury CT, US
Christopher M. Dye - San Diego CA, US
William K. Ackermann - East Hartford CT, US
Stephen P. Muron - Columbia CT, US
loannis Alvanos - West Springfield MA, US
Brian D. Merry - Andover CT, US
Arthur M. Salve - Tolland CT, US
James W. Norris - Lebanon CT, US
International Classification:

F01D 5/08
US Classification:

415115, 416 97 R
Abstract:

A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.

Gas Turbine Engine With High Speed Low Pressure Turbine Section And Bearing Support Features
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US Patent:

20130192191, Aug 1, 2013
Filed:

Apr 25, 2012
Appl. No.:

13/455235
Inventors:

Frederick M. Schwarz - Glastonbury CT, US
Daniel Bernard Kupratis - Wallingford CT, US
Brian D. Merry - Andover CT, US
Gabriel L. Suciu - Glastonbury CT, US
William K. Ackermann - East Hartford CT, US
International Classification:

F02G 3/00
US Classification:

60 3915
Abstract:

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

Gas Turbine Engine With High Speed Low Pressure Turbine Section
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US Patent:

20130192196, Aug 1, 2013
Filed:

Jan 31, 2012
Appl. No.:

13/363154
Inventors:

Gabriel L. Suciu - Glastonbury CT, US
William K. Ackermann - East Hartford CT, US
Daniel Bernard Kupratis - Wallingford CT, US
Frederick M. Schwarz - Glastonbury CT, US
International Classification:

F02K 3/02
US Classification:

602261
Abstract:

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Gas Turbine Engine Buffer System
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US Patent:

20130192239, Aug 1, 2013
Filed:

Jan 31, 2012
Appl. No.:

13/362349
Inventors:

Jorn A. Glahn - Manchester CT, US
William K. Ackermann - East Hartford CT, US
Clifton J. Crawley - Glastonbury CT, US
Philip S. Stripinis - Rocky Hill CT, US
International Classification:

F02C 7/12
F02C 6/08
US Classification:

60772, 60785
Abstract:

A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine.

Gas Turbine Engine Buffer System
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US Patent:

20130192248, Aug 1, 2013
Filed:

Feb 6, 2012
Appl. No.:

13/366445
Inventors:

William K. Ackermann - East Hartford CT, US
Philip S. Stripinis - Rocky Hill CT, US
International Classification:

F02C 7/047
F02C 6/08
US Classification:

60779, 60785
Abstract:

A gas turbine engine includes a buffer system. The buffer system can include a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the buffer supply air at an acceptable temperature to anti-ice the hardware of said fan section.

Gas Turbine Engine Buffer System
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US Patent:

20130192250, Aug 1, 2013
Filed:

Jan 31, 2012
Appl. No.:

13/362288
Inventors:

Jorn A. Glahn - Manchester CT, US
Clifton J. Crawley - Glastonbury CT, US
Philip S. Stripinis - Rocky Hill CT, US
William K. Ackermann - East Hartford CT, US
International Classification:

F02C 6/08
US Classification:

60782, 60785
Abstract:

A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure. The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air.

Gas Turbine Engine Buffer System
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US Patent:

20130192252, Aug 1, 2013
Filed:

Feb 6, 2012
Appl. No.:

13/366447
Inventors:

William A. ACKERMANN - East Hartford CT, US
Peter M. MUNSELL - Granby CT, US
International Classification:

F02C 6/08
US Classification:

60782, 60785
Abstract:

A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

Gas Turbine Engine Buffer System Providing Zoned Ventilation
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US Patent:

20130192253, Aug 1, 2013
Filed:

Feb 6, 2012
Appl. No.:

13/366450
Inventors:

William K. ACKERMANN - East Hartford CT, US
Philip S. STRIPINIS - Rocky Hill CT, US
International Classification:

F02C 6/08
US Classification:

60782, 60785
Abstract:

A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can communicate a bleed air to the second zone.