Erik N Johnson

US Patent:

20180298763, Oct 18, 2018

Filed:

Nov 11, 2014

Appl. No.:

15/525820

Inventors:

- München, DE
Jae Y. Um - Winter Garden FL, US
Gerald L. Hillier - Charlottesville VA, US
Eric Schroeder - Loveland OH, US
Erik Johnson - Cedar Park TX, US
Dustin Muller - Cincinnati OH, US

International Classification:

F01D 5/18
F01D 5/20

Abstract:

The present disclosure provides a turbine blade () comprising a leading edge cooling circuit (), a trailing edge cooling circuit (), a mid-section cooling circuit () comprising a first channel (), an intermediate channel (), and a final channel (), and an axial tip cooling circuit (). The leading edge, mid-section, and trailing edge cooling circuits () each receive a cooling airflow (C) from a cooling air supply. A radially outer portion of each of the leading edge and mid-section cooling circuits () further comprises at least one outlet () in fluid communication with the axial tip cooling circuit () such that substantially all of a leading edge cooling airflow (LE) exiting the leading edge cooling circuit () and substantially all of a mid-section cooling airflow (MS) exiting the mid-section cooling circuit () is directed to the axial tip cooling circuit ().

US Patent:

20170275998, Sep 28, 2017

Filed:

Sep 18, 2014

Appl. No.:

15/508497

Inventors:

- München, DE
Jae Y. Um - Winter Garden FL, US
Gerald L. Hillier - Charlottesville VA, US
Wayne J. McDonald - Charlotte NC, US
Erik Johnson - Cedar Park TX, US
Anthony Waywood - Cincinnati OH, US
Eric Schroeder - Loveland OH, US
Zhengxiang Pu - Oviedo FL, US

Assignee:

Siemens Aktiengesellschaft - Muenchen

International Classification:

F01D 5/18
F01D 25/12
F01D 9/02

Abstract:

A core structure () includes a first core element () including a leading edge section (), a tip section (), and a turn section () joining the leading edge and tip sections (). The first core element () is adapted to be used to form a leading edge cooling circuit () in a gas turbine engine airfoil (). The leading edge cooling circuit () includes a cooling fluid passage () having a leading edge portion () formed by the first core element leading edge section (), a tip portion () formed by the first core element tip section (), and a turn portion () formed by the first core element turn section (). Each of the leading edge portion (), the tip portion (), and the turn portion () of the cooling fluid passage () are formed concurrently in the airfoil () by the first core element ().

US Patent:

20170218787, Aug 3, 2017

Filed:

Feb 18, 2016

Appl. No.:

15/118510

Inventors:

- München, DE
Gm Salam Azad - Oviedo FL, US
Zhihong Gao - Orlando FL, US
Erik Johnson - Cedar Park TX, US
Eric Schroeder - Loveland OH, US
Nicholas F. Martin, Jr. - York SC, US

International Classification:

F01D 11/12
F01D 25/24
F01D 5/12

Abstract:

Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.

US Patent:

20150204197, Jul 23, 2015

Filed:

Jan 23, 2014

Appl. No.:

14/161817

Inventors:

- München, DE
Jae Y. Um - Winter Garden FL, US
Gerald L. Hillier - Charlottesville VA, US
Eric Schroeder - Loveland OH, US
Erik Johnson - Cincinnati OH, US

International Classification:

F01D 5/18
F01D 9/02

Abstract:

An airfoil cooling arrangement (), including: a leading edge chamber () configured to cool an interior surface () of an airfoil; and an impingement orifice () configured to direct an impingement jet () toward an impingement location () disposed on the interior surface and offset from a camber line () of the airfoil The airfoil cooling arrangement is effective to guide post impingement cooling fluid along the interior surface, through a leading portion () of the leading edge chamber, and then back toward a trailing edge () of the airfoil in a helical motion (). A stagnation region () is formed adjacent the interior surface and on a trailing edge side of the impingement location, and a relatively high static pressure associated therewith is effective to contribute to the helical motion () of the post impingement cooling fluid within the leading edge chamber