James Piper

US Patent:

8166763, May 1, 2012

Filed:

Sep 13, 2007

Appl. No.:

11/898609

Inventors:

James Scott Piper - El Cajon CA, US
Hongyu Wang - San Diego CA, US

Assignee:

Solar Turbines Inc. - San Diego CA

International Classification:

F02K 1/00

US Classification:

60737, 60740, 60742

Abstract:

A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel inlets, one or more fuel galleries annularly disposed about the longitudinal axis, and an air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the air inlet at the proximal end, and configured to mechanically couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a pilot assembly disposed radially inwards of the premix barrel. The pilot assembly may include a first end and a second end. The second end is removably coupled to the injector housing, and the first end is proximate the distal end of the premix barrel.

US Patent:

8286433, Oct 16, 2012

Filed:

Oct 26, 2007

Appl. No.:

11/976641

Inventors:

James Scott Piper - El Cajon CA, US
Hongyu Wang - San Diego CA, US

Assignee:

Solar Turbines Inc. - San Diego CA

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60742, 60740, 60748, 60739

Abstract:

A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and is configured to couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end. The second end is coupled to the injector housing and the first end is located proximate the distal end of the premix barrel. The fuel injector further includes a pilot liquid tube having a third end and a fourth end disposed radially inwards of the pilot assembly.

US Patent:

8393155, Mar 12, 2013

Filed:

Nov 28, 2007

Appl. No.:

11/987251

Inventors:

James Scott Piper - El Cajon CA, US
Hongyu Wang - San Diego CA, US

Assignee:

Solar Turbines Incorporated - San Diego CA

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60742, 60739, 60748

Abstract:

A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem.

US Patent:

45763330, Mar 18, 1986

Filed:

Aug 3, 1981

Appl. No.:

6/289401

Inventors:

James R. Piper - Villa Park CA

International Classification:

F24F 706
F24F 3044
F24F 308
F24D 504

US Classification:

237 49

Abstract:

A system for space heating for a building employing structural elements of the building as heating conduits. Girder pairs are employed as manifold conduits and joist pairs are employed as distribution conduits for the present system. The crawl space of the building is used for the return air and becomes a plenum therefor.

US Patent:

20170298884, Oct 19, 2017

Filed:

Apr 15, 2016

Appl. No.:

15/130058

Inventors:

- San Diego CA, US
Ram Srinivasan - San Diego CA, US
James Piper - Bonita CA, US
Raymond Alvarez - La Mesa CA, US
Rasoul Paydar - San Diego CA, US

Assignee:

Solar Turbines Incorporated - San Diego CA

International Classification:

F02M 61/16
F02M 43/04

Abstract:

A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe numbers and compositions.

US Patent:

20170191421, Jul 6, 2017

Filed:

Jan 5, 2016

Appl. No.:

14/988588

Inventors:

- SAN DIEGO CA, US
DONALD JAMES CRAMB - SAN DIEGO CA, US
JAMES SCOTT PIPER - SAN DIEGO CA, US
MICHAEL JOHN RAMOTOWSKI - SAN DIEGO CA, US

Assignee:

SOLAR TURBINES INCORPORATED - SAN DIEGO CA

International Classification:

F02C 7/22
F23R 3/28

Abstract:

A fuel injector for a gas turbine engine is disclosed. The fuel injector includes a flange assembly with a distribution block, three main gas tubes, and an injector head. The distribution block evenly distributes a main gas fuel to the three main gas tubes. The injector head includes an injector body with a primary gas gallery including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block and the primary gas gallery. The three main gas tubes are all in flow communication with the primary gas gallery and provide the main gas fuel from the same main gas fuel source.

US Patent:

20170191428, Jul 6, 2017

Filed:

Jan 5, 2016

Appl. No.:

14/988562

Inventors:

- SAN DIEGO CA, US
Donald James Cramb - San Diego CA, US
James Scott Piper - San Diego CA, US
Michael John Ramotowski - San Diego CA, US

Assignee:

SOLAR TURBINES INCORPORATED - SAN DIEGO CA

International Classification:

F02C 9/40
F02C 7/22

Abstract:

A method for lean direct injection of a liquid fuel from a fuel injector into a combustion chamber of a gas turbine engine is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber through a pilot liquid fuel circuit during light off and during acceleration towards idle. The method also includes injecting the liquid fuel in two streams including injecting a majority of the liquid fuel as an annular film through a main liquid fuel circuit and injecting a remainder of the liquid fuel through the pilot liquid fuel circuit when the gas turbine engine is at idle and for operating ranges of the gas turbine engine above idle.

US Patent:

20170191457, Jul 6, 2017

Filed:

Jan 5, 2016

Appl. No.:

14/988574

Inventors:

- SAN DIEGO CA, US
DONALD JAMES CRAMB - SAN DIEGO CA, US
JAMES SCOTT PIPER - SAN DIEGO CA, US
MICHAEL JOHN RAMOTOWSKI - SAN DIEGO CA, US

Assignee:

SOLAR TURBINES INCORPORATED - SAN DIEGO CA

International Classification:

F02M 61/16
F23R 3/28
F02M 61/18

Abstract:

A center body assembly for a fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, swirl slots, and a prefilm passage. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end and a gallery inlet end that aligns with the primary liquid passage. The liquid gallery tapers down from the gallery inlet end to the gallery discharge end. The swirl slots extend from the liquid gallery to the prefilm passage in a helical pattern. The prefilm passage includes an annular shape that turns inward towards an assembly axis of the center body assembly.