Jason Paul Hoppa

US Patent:

7637110, Dec 29, 2009

Filed:

Nov 30, 2005

Appl. No.:

11/290115

Inventors:

Robert P. Czachor - Cincinnati OH, US
James Anthony Groeschen - Burlington KY, US
Jason Paul Hoppa - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/20

US Classification:

60796, 415136, 60800

Abstract:

A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine, where the position of the pins relative to the second structure is adjustable.

US Patent:

62057634, Mar 27, 2001

Filed:

May 24, 1999

Appl. No.:

9/317243

Inventors:

Gilbert Farmer - Cincinnati OH
James A. Groeschen - Burlington KY
Jason P. Hoppa - Springdale OH
Stanford P. Seto - Loveland OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C13/10

US Classification:

60 3902

Abstract:

A method for determining the appropriate hole parameters to achieve the desired airflow in a swirler with as-cast air jet holes includes the steps of determining the desired airflow through the holes and selecting a hole angle for the holes. Next, the ratio of the hole exit area to the hole inlet area is calculated based on the desired airflow and the selected hole angle using a regression equation. Then a value is determined for either of the hole exit area or the hole inlet area, and the other area is calculated from the known ratio. Once the hole angle, hole exit area and hole inlet area have been determined, then a swirler can be cast with as-cast holes using these hole parameters.

US Patent:

20200318831, Oct 8, 2020

Filed:

Jun 19, 2020

Appl. No.:

16/907013

Inventors:

- Schenectady NY, US
Stephen Gerard Schadewald - Clifton Park NY, US
Jason Paul Hoppa - West Chester OH, US
Kirk Douglas Gallier - Liberty Township OH, US
Christopher Edward Wolfe - Niskayuna NY, US
Robert Proctor - Mason OH, US

International Classification:

F23R 3/00
F16J 15/16
F23R 3/60
F16J 15/44
F01D 9/02

Abstract:

A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (P) bypass airflow exiting a compressor to the cavity. The high-pressure (P) bypass airflow exerting a radial force on the piston ring.

US Patent:

20180306120, Oct 25, 2018

Filed:

Apr 21, 2017

Appl. No.:

15/493549

Inventors:

- Schenectady NY, US
Stephen Gerard Schadewald - Clifton Park NY, US
Jason Paul Hoppa - West Chester OH, US
Kirk Douglas Gallier - Liberty Township OH, US
Christopher Edward Wolfe - Niskayuna NY, US
Robert Proctor - Mason OH, US

International Classification:

F02C 7/28
F16J 15/16
F16J 15/34
F02C 3/04
F23R 3/00
F01D 9/02
F02C 9/18

Abstract:

A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (P) bypass airflow exiting a compressor to the cavity. The high-pressure (P) bypass airflow exerting a radial force on the piston ring.