Erik J Johnson

US Patent:

20180038233, Feb 8, 2018

Filed:

Mar 17, 2015

Appl. No.:

15/552882

Inventors:

- Orlando FL, US
Caleb Myers - Cincinnati OH, US
Erik Johnson - Cedar Park TX, US
Steven Koester - Toledo OH, US

International Classification:

F01D 5/18

Abstract:

An airfoil () is disclosed for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more converging-diverging exit slots () configured to increase the effectiveness of the cooling system () at the trailing edge () of the airfoil () by increasing the contact of cooling fluids with internal surfaces () of the pressure and suction sides () of the airfoil (). In at least one embodiment, the trailing edge cooling channel () may include one or more converging-diverging exit slots () to further pressurize the trailing edge cooling channel () and may be formed by a first and second ribs () extending between an outer walls () forming the pressure and suction sides (). The converging-diverging exit slot () may be formed from a first converging section () having an inlet () with a larger cross-sectional area than an outlet () and is formed from a second diverging section () having an inlet () with a smaller cross-sectional area than an outlet ().

US Patent:

20170370231, Dec 28, 2017

Filed:

Jan 28, 2015

Appl. No.:

15/544034

Inventors:

- Orlando FL, US
Anthony Waywood - Cincinnati OH, US
Erik Johnson - Cedar Park TX, US
Steven Koester - Toledo OH, US

International Classification:

F01D 5/18
F01D 5/30

Abstract:

A cooling system () for a turbine airfoil () of a turbine engine having one or more mid-chord cooling channels () that extend through both the airfoil () and a platform () of the airfoil () to provide adequate cooling the platform () while cooling the airfoil () is disclosed. The mid-chord cooling channel () may be formed from an airfoil portion () extending generally spanwise within the airfoil () and a platform portion () extending into a platform () of the airfoil () with a larger cross-sectional area than a cross-sectional area of the airfoil portion (). The mid-chord cooling channel () may also extend into the platform () of the airfoil () a distance laterally outside of a silhouette () of the airfoil () defined by the leading edge (), trailing edge (), pressure side () and suction side () of the airfoil (). Thus, the mid-chord cooling channel () extends laterally into the platform () to provide adequate cooling the platform ().

US Patent:

20140205443, Jul 24, 2014

Filed:

Feb 25, 2014

Appl. No.:

14/189227

Inventors:

- Munchen, DE
Eric Schroeder - Loveland OH, US
Erik Johnson - Cincinnati OH, US
Dustin Muller - Cincinnati OH, US
Steven Coppess - Cincinnati OH, US
Manjit Shivanand - Winter Springs FL, US
Kahwai G. Muriithi - Greenville SC, US

Assignee:

Siemens Aktiengesellschaft - Munchen

International Classification:

F02C 7/28

US Classification:

4151701

Abstract:

A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.