Brandon E Snyder

US Patent:

20200208533, Jul 2, 2020

Filed:

Dec 27, 2018

Appl. No.:

16/233964

Inventors:

- Indianapolis IN, US
Ryan C. Humes - Indianapolis IN, US
Brandon R. Snyder - Greenwood IN, US

International Classification:

F01D 11/18
F02K 3/06
F01D 25/12
F02C 9/18

Abstract:

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

US Patent:

20180320524, Nov 8, 2018

Filed:

May 2, 2017

Appl. No.:

15/584946

Inventors:

- Indianapolis IN, US
Brandon Snyder - Greenwood IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/06
F01D 11/00

Abstract:

A rotor stack assembly and method of assembling same. The rotor stack assembly comprises a tie bolt, at least one rotor disk, and a stub shaft. The rotor disk and stub shaft are carried by the tie bolt. The stub shaft is threadably engaged with a threaded end of the tie bolt and comprises a rotatable seal member and an engagement surface for contacting the rotor disk. Engagement of the stub shaft with tie bolt allows for tensioning and pre-loading of the tie bolt to desired levels.

US Patent:

20180320532, Nov 8, 2018

Filed:

May 2, 2017

Appl. No.:

15/584929

Inventors:

- Indianapolis IN, US
Brandon Snyder - Greenwood IN, US
James Sellhorn - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/30
F01D 11/00

Abstract:

A cover plate for maintaining axial alignment between a blade assembly and a rotor disk and transferring centrifugal loading directly to the rotor disk. The cover plate comprises a plate key extending axially from an elongate member, the plate key configured to engage a keyway of the rotor disk assembly and/or a notch of the blade key.

US Patent:

20170114650, Apr 27, 2017

Filed:

Oct 26, 2015

Appl. No.:

14/922844

Inventors:

- Indianapolis IN, US
Brandon R. Snyder - Greenwood IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F01D 5/30

Abstract:

In accordance with some embodiments of the present disclosure, a gas turbine engine is presented. The engine has at least one turbine stage and each stage has a turbine disc concentric with the axis of the engine. The turbine disc has a turbine arm positioned axially from the disc and rigidly attached thereto. The drive arm is also concentric with the turbine axis and has an outer surface. The turbine stage also has a cover plate concentric with the turbine axis and covering at least a portion of the turbine disc. An arrangement of turbine blades are positioned around the periphery of the disc and are retained on the turbine disc at least partially by the cover plate. The system includes a spanner nut, and threads on a portion of the turbine drive arm. The spanner nut it threaded onto the turbine arm which applies an axial force on the cover plate, thereby retaining the cover plate.

US Patent:

20140356177, Dec 4, 2014

Filed:

Dec 11, 2013

Appl. No.:

14/103106

Inventors:

- Indianapolis IN, US
Brandon R. Snyder - Indianapolis IN, US

Assignee:

Rolls-Royce North American Technologies, Inc. - Indianapolis IN

International Classification:

F01D 5/30
B23P 15/04
F01D 5/32

US Classification:

416220 R, 2988921

Abstract:

An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.