Daniel K Morrison

US Patent:

20100166546, Jul 1, 2010

Filed:

Dec 22, 2009

Appl. No.:

12/644999

Inventors:

Vance A. Mahan - Martinsville IN, US
Daniel K. Morrison - Carmel IN, US
Adam J. Morrison - Greenwood IN, US

International Classification:

F02C 7/00
B23P 11/00

US Classification:

4151994, 2988921

Abstract:

One embodiment is an apparatus comprising a first rotational gas turbine engine component including first threads; a second rotational gas turbine engine component including second threads; the first threads and the second threads being mated; and the first rotational engine component being fastened to the second rotational engine component substantially only by the first threads and the second threads being mated. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engine interconnection. Further exemplary embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention are included in the following description, drawings, and claims.

US Patent:

20110158811, Jun 30, 2011

Filed:

Nov 22, 2010

Appl. No.:

12/951306

Inventors:

Daniel K. Morrison - Carmel IN, US

International Classification:

F01D 5/30

US Classification:

416204 R

Abstract:

A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform attached to the airfoil on one side, the other side being attached to a stalk having a lower attachment portion useful for being received in a compressor disk. The blade includes an undercut beneath a portion of the airfoil, preferably beneath the leading edge and/or trailing edge of the airfoil. In one form the undercut is located in a corner of the platform and extends partially along two sides of the platform.

US Patent:

20170114651, Apr 27, 2017

Filed:

Oct 26, 2015

Appl. No.:

14/922932

Inventors:

- Indianapolis IN, US
Daniel K. Morrison - Carmel IN, US
Matthew Basiletti - Lafayette IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/30

Abstract:

A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. The second disc includes an arrangement of turbine blade inserts positioned around its periphery. This arrangement is concentric with the plurality of turbine discs. Turbine blade inserts are retained on the second disc at least in part by the cover plate. The engine further comprises a coaxial tie bolt extending through the plurality of coaxial turbine discs, a spanner nut on the end of the tie bold, an arm coaxial with the axis extending from the face of the second disc having a distal end an axial stop extending from the face of the first disc. The distal end is in contact with the axial stop. The axial stop retains the axial movement of the second disc. The cover plate extends axially between the axial stop and the second disc and radially between the arm and the periphery of the second disc.