Lawrence E Portlock

US Patent:

7959532, Jun 14, 2011

Filed:

Dec 1, 2004

Appl. No.:

11/718519

Inventors:

Gabriel L. Suciu - Glastonbury CT, US
Lawrence E. Portlock - Bethany CT, US
Brian Merry - Andover CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F03G 7/00
F16H 57/08

US Classification:

475331, 475346, 60721

Abstract:

A hydraulic seal for a tip turbine engine includes an inner radial flange and an outer radial flange. The inner radial flange rotates relative to the outer radial seal section and the planet carrier face to prevent lubrication from entering into the air flow streams within the engine without additional engine assembly procedures.

US Patent:

7976272, Jul 12, 2011

Filed:

Dec 1, 2004

Appl. No.:

11/719911

Inventors:

Gabriel L. Suciu - Glastonbury CT, US
Lawrence E. Portlock - Bethany CT, US
Brian Merry - Andover CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 25/12

US Classification:

415126, 415144, 60 3943

Abstract:

A compressor for a turbine engine includes an inflatable bleed valve that selectively bleeds core airflow from the compressor. The bleed valve has an inlet leading from the compressor and a passageway leading from the inlet. An inflatable valve selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve.

US Patent:

8020665, Sep 20, 2011

Filed:

Nov 22, 2006

Appl. No.:

11/603393

Inventors:

William G. Sheridan - Southington CT, US
Lawrence E. Portlock - Bethany CT, US
Michael E. McCune - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01M 1/18
F16H 57/04

US Classification:

184 612, 184 64

Abstract:

A lubrication system, includes an auxiliary lubricant tank and a supply conduit extending from a source of lubricant and through the auxiliary lubricant tank. A portion of the conduit resides within the tank and has an opening for allowing lubricant transfer between the tank and the conduit.

US Patent:

8083030, Dec 27, 2011

Filed:

Dec 1, 2004

Appl. No.:

11/718521

Inventors:

Lawrence E. Portlock - Bethany CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F16H 57/04
F01D 25/18
F02C 7/06

US Classification:

184 611, 184 6, 475159

Abstract:

An oil system () for a tip turbine engine () includes an annular lubricating fluid plenum () which sprays lubricating fluid through a multitude of lubricating fluid passages () and into the multitude of passages () located within a gearbox assembly () as they revolve thereby. Lubricating fluid is thereby communicated directly into the gearbox assembly () and returned to a sump tank () through a multitude of drain passages.

US Patent:

8215454, Jul 10, 2012

Filed:

Nov 22, 2006

Appl. No.:

11/603664

Inventors:

Lawrence E. Portlock - Bethany CT, US
Michael E. McCune - Colchester CT, US
Louis J. Dobek - Somers CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F16H 57/04
F01D 25/18

US Classification:

184 612, 184 611, 184 62, 184 64, 475159, 74468

Abstract:

A lubrication system includes an auxiliary lubricant tank , a supply conduit extending from a source of lubricant to the auxiliary lubricant tank. A reduced-G bypass line branches from the conduit and enters the auxiliary tank at a first elevation E. The system also includes an auxiliary tank discharge conduit , a portion of which resides within the tank. The resident portion has an opening at least partially at a second elevation Ehigher than the first elevation.

US Patent:

8267826, Sep 18, 2012

Filed:

Mar 15, 2005

Appl. No.:

11/080175

Inventors:

Loc Quang Duong - South Windsor CT, US
Lawrence E. Portlock - Bethany CT, US
Michael E. McCune - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F16H 57/04
F16H 57/08

US Classification:

475159, 475331

Abstract:

A planetary carrier includes a journal bearing for supporting a planetary gear. The journal bearing receives lubricant to produce a lubricant film to support gear loads. A torque frame is attached to the carrier housing to transmit torque and to prevent twisting of the carrier housing. The torque frame includes several lubricant communication passages to provide lubricant to each of the separate journal bearings. Each of the lubricant communication passages includes an accumulator for storing lubricant during normal operation. The accumulator stores a desired amount of lubricant to provide lubricant to the adjacent journal bearing for the interim period between primary system stoppage and reestablishment of lubricant flow by a secondary system.

US Patent:

8292570, Oct 23, 2012

Filed:

Jan 25, 2008

Appl. No.:

12/019919

Inventors:

Gabriel L. Suciu - Glastonbury CT, US
Om P. Sharma - South Windsor CT, US
Lawrence E. Portlock - Bethany CT, US
Brian D. Merry - Andover CT, US
Shankar S. Magge - South Windsor CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 1/24

US Classification:

415 68, 415 69

Abstract:

A low pressure turbine for a gas turbine engine includes inner and outer counter-rotating rotor sets, with both said rotor sets driving a common shaft.

US Patent:

8484942, Jul 16, 2013

Filed:

May 30, 2012

Appl. No.:

13/483657

Inventors:

Michael E. McCune - Colchester CT, US
William G. Sheridan - Southington CT, US
Lawrence E. Portlock - Bethany CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 7/06
F16C 19/00
B23Q 11/12
F16H 57/04
F16H 57/08

US Classification:

60 3908, 384473, 384475, 184 612, 184 614, 475159, 475331, 602261

Abstract:

A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.