DR. DANIEL JAMES BROWN, M.D.
Osteopathic Medicine at University Dr, Hamilton, OH

6553767, Apr 29, 2003

Jun 11, 2001

09/878836

Gilbert Farmer - Cincinnati OH
Daniel D. Brown - Fairfield OH
Myron E. Rutherford - Cincinnati OH
Steven C. Vise - Cincinnati OH
Jeffrey M. Martini - Liberty Township OH

General Electric Company - Schenectady NY

F02C 314

60752, 2989001

An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction. The shell is machined from a single piece integrally formed near net shape form such as a forging, a casting, or more particularly a spin or centrifugal casting. The invention includes a method for making the annular gas turbine engine combustor liner by forming a single piece integrally formed near net shape form and machining it to produce the shell and the above features in the shell.

6655149, Dec 2, 2003

Dec 17, 2002

10/321088

Gilbert Farmer - Cincinnati OH
Daniel Dale Brown - Fairfield OH
Myron Edward Rutherford - Cincinnati OH

General Electric Company - Schenectady NY

F01D 2512

60754

A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.

6513331, Feb 4, 2003

Aug 21, 2001

09/934182

Daniel Dale Brown - Fairfield OH
Gilbert Farmer - Cincinnati OH
Myron Edward Rutherford - Cincinnati OH

General Electric Company - Schenectady NY

F02C 304

60754

A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.

6655146, Dec 2, 2003

Jul 31, 2001

09/919028

Ella Christine Kutter - Miamisburg OH
Thomas Anthony Leen - Cincinnati OH
Daniel Dale Brown - Fairfield OH
Craig Douglas Young - Maineville OH
Gilbert Farmer - Cincinnati OH
Mohammad Ehteshami - Mason OH

General Electric Company - Schenectady NY

F23R 306

60752, 60754, 60755, 60757

A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.

6758045, Jul 6, 2004

Aug 30, 2002

10/233356

Mina Dimov - Cincinnati OH
Paul R. Angel - Fairfield OH
Steven Marakovits - Mason OH
Daniel Dale Brown - Fairfield OH

General Electric Company - Schenectady NY

F02C 314

60804, 60747, 60772

A method enables a gas turbine engine multi-domed combustor including an outer liner and an inner liner that define a combustion chamber therebetween to be assembled. The method comprises coupling a first dome including a heat shield that includes an annular endbody that extends a first distance axially from the heat shield to the combustor outer liner, and coupling a second dome including a heat shield that includes an annular endbody that extends a second distance axially from the heat shield to the first dome, such that the second dome is radially aligned with respect to the first dome, and wherein the second dome second distance is less than the first dome first distance.

2013000, Jan 3, 2013

Jun 30, 2011

13/174027

Daniel Dale Brown - Cincinnati OH, US
Glenn Edward Wiehe - West Chester OH, US
Michael Terry Bucaro - Cincinnati OH, US
Stephen William Freund - Cincinnati OH, US

GENERAL ELECTRIC COMPANY - Schenectady NY

F23D 14/62, B21D 53/00

431354, 2989002

A combustor dome assembly includes a dome plate with upstream and downstream faces and an aperture therein; a deflector with body and a tube section, the deflector fixedly attached to the dome plate adjacent the downstream face with the tube section in the aperture; a retainer having an annular body with a central opening therein, an annular flange, and at least one hook defining a slot, the retainer being fixedly attached to the dome plate adjacent the upstream face of the dome plate with the flange received in the aperture; and an annular mixer with a radial array of swirl vanes and an annular mounting flange, with a retention tab extending radially outward from the mounting flange. The mixer is disposed adjacent the upstream face with the mounting flange against the retainer. The retention tab is engaged in the slot to prevent axial withdrawal of the mixer from the retainer.

5682747, Nov 4, 1997

Apr 10, 1996

8/627811

Daniel D. Brown - Fairfield OH
Marlin S. Brueggert - Lebanon IN
Ronald T. Murach - Mason OH
Kevin W. Raabe - Cincinnati OH
Joseph G. Sabato - Hamilton OH

General Electric Company - Cincinnati OH

F02C 100

60746

A heat shield for a gas turbine engine combustor of the type composed of multiple annular stages. The heat shield is particularly adapted for use in a middle stage disposed between radially inward and outward stages of a multistage combustor, and configured to form centerbodies that isolate the middle stage from the other stages of the combustor. The heat shield is composed of an annular array of single crystal superalloy segments. To achieve acceptable levels of durability for the superalloy segments, their primary and secondary crystal orientations are controlled to achieve a balance between the ability to withstand thermally-induced stresses and those stresses induced by high levels of acoustic energy, particularly those high levels attained as a result of a combustor operating with lean fuel/air ratios.

7856826, Dec 28, 2010

Nov 10, 2006

11/558652

Daniel Dale Brown - Cincinnati OH, US
Michael Terry Bucaro - Liberty Township OH, US
Jeff Martini - Liberty Township OH, US

General Electric Company - Schenectady NY

F02C 1/00, F02G 3/00

60752, 60796, 60798, 60800, 60758, 60804

A method of assembling a combustor for use in a turbine engine is disclosed. The method includes providing a dome assembly ring including a plurality of assembly ring openings, positioning a plurality of elongated rings on the dome assembly ring, providing a cowl assembly including an inner cowl portion and an outer cowl portion that are fabricated from sheet metal, and coupling the inner and outer cowl portions to the dome assembly ring such that each of the plurality of elongated rings is coupled to the dome assembly ring.

7765809, Aug 3, 2010

Nov 10, 2006

11/558636

Daniel Dale Brown - Cincinnati OH, US
Michael Terry Bucaro - Liberty Township OH, US

General Electric Company - Schenectady NY

F02C 1/00, F02G 3/00

60752, 60796

A method of assembling a dome assembly for use in a turbine engine combustor is disclosed. The method includes providing a dome assembly ring, an inner liner portion, and an outer liner portion. The method also includes coupling the inner liner portion and the outer liner portion to the dome assembly ring, positioning a plurality of rings on the dome assembly ring, and coupling at least one of an inner cowl and an outer cowl to the dome assembly ring such that each of the plurality of rings and at least one of the inner and outer cowls are removable without uncoupling the dome assembly ring from either the inner or outer liner portions.