Myron E Rutherford

US Patent:

6553767, Apr 29, 2003

Filed:

Jun 11, 2001

Appl. No.:

09/878836

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 314

US Classification:

60752, 2989001

Abstract:

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.

US Patent:

6620457, Sep 16, 2003

Filed:

Jul 13, 2001

Appl. No.:

09/905798

Inventors:

Gilbert Farmer - Cincinnati OH
Thomas John Tomlinson - West Chester OH
Raymond William Heidorn - Fairfield OH
Jeffrey Arnold Fehrenbach - Cincinnati OH
William Lee Imhoff - Hamilton OH
Myron Edward Rutherford - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 102

US Classification:

427235, 427273, 427427, 427256

Abstract:

A method of applying a thermal barrier coating system to a metal piece having cooling holes angled in a first direction and cooling holes angled in a second direction. The method includes spraying a bond coat on a first surface of the piece at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the bond coat from entirely filling any of the holes. A thermal barrier coating is sprayed on the bond coat at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the thermal barrier coating from entirely filling any of the holes. The method also includes spraying a high pressure fluid jet from a nozzle assembly through each hole generally parallel to the respective cooling hole.

US Patent:

6655149, Dec 2, 2003

Filed:

Dec 17, 2002

Appl. No.:

10/321088

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 2512

US Classification:

60754

Abstract:

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.

US Patent:

6513331, Feb 4, 2003

Filed:

Aug 21, 2001

Appl. No.:

09/934182

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 304

US Classification:

60754

Abstract:

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.