Barton M Pepperman

8485785, Jul 16, 2013

Jul 19, 2007

11/879923

Chad M. Garner - Orlando FL, US
Barton M. Pepperman - Winter Springs FL, US

Siemens Energy, Inc. - Orlando FL

F01D 5/30
F01D 5/16

416221, 416500

A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member.

20120207586, Aug 16, 2012

Feb 15, 2011

13/027354

Abdullatif M. Chehab - Oviedo FL, US
Kevin L. Hines - Sorrento FL, US
Barton M. Pepperman - Winter Springs FL, US
Matthew D. Bogdan - Orlando FL, US

F01D 25/00
G01B 1/00
G01M 15/14

415118, 7311201, 33656

A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.

53583795, Oct 25, 1994

Oct 27, 1993

8/141756

Barton M. Pepperman - Orlando FL
Andrew J. Ayoob - Oviedo FL

Westinghouse Electric Corporation - Pittsburgh PA

F04D 2944

415191

A vane for the turbine section of a gas turbine has an airfoil portion with leading edge, center and trailing edge portions. The leading edge portion is attached to the center portion by a dove tail joint that allows the leading edge portion to slide in the radial direction with respect to the center portion while preventing movement in the axial and circumferential directions, thereby eliminating thermal stresses created by differential thermal expansion between the leading edge portion and the remainder of the vane. An opening in the vane inner shroud that is normally sealed by a closure plate allows the leading edge portion to be readily replaced in the event of damage. The leading edge portion may be formed from a ceramic material and need not be supplied with cooling air.

56392168, Jun 17, 1997

Feb 26, 1996

8/606909

Leroy D. McLaurin - Winter Springs FL
Barton M. Pepperman - Orlando FL

Westinghouse Electric Corporation - Pittsburgh PA

F01D 508

416 95

A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling air and then extend axially along almost the entire length of the platform. Each passage also has an outlet formed in the downstream face of the platform that allows the cooling air to exit the platform and enter the hot gas flow path. The passages are formed in portions of the platform that overhang the shank portion of root.

20170218788, Aug 3, 2017

Oct 23, 2014

15/515169

- Orlando FL, US
Barton M. Pepperman - Winter Springs FL, US

F01D 11/18
F01D 11/02

A gas turbine engine () having a turbine blade tip clearance control system () for increasing the efficiency of the engine () by reducing the gap () between turbine blade tips () and radially outward ring segments () is disclosed. The turbine blade tip clearance control system () may include one or more clearance control bands () positioned radially outward of inner surfaces () of ring segments () and bearing against at least one outer surface () of the ring segments () to limit radial movement of the ring segments (). During operation, the clearance control band () limits radial movement of the ring segments (), and the turbine blade tips () do not have a pinch point during start-up transient conditions. In addition, the smallest gap () during turbine engine operation may be found at steady state operation of the gas turbine engine (). Thus, the clearance control system () can set the gap () between turbine blade tips () and ring segments () to be zero at steady state operation.

20170089352, Mar 30, 2017

Sep 30, 2015

14/870838

- Munchen, DE
Barton M. Pepperman - Winter Springs FL, US

F04D 29/16
F04D 29/52
F04D 29/54

A high-efficiency compressor section () for a gas turbine engine is disclosed. The compressor section includes a vane carrier () adapted to hold ring segment assemblies () that provide optimized blade tip gaps () during a variety of operating conditions. The ring segment assemblies include backing elements () and tip-facing elements () urged into a preferred orientation by biasing elements () that maintain contact along engagement surfaces (). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap () therebetween, resulting in blade tip gaps that are dynamically adjusted operation.

20170089353, Mar 30, 2017

Sep 30, 2015

14/870875

- Munchen, DE
Barton M. Pepperman - Winter Springs FL, US

F04D 29/16
F04D 29/52
F04D 29/54

A high-efficiency compressor section () for a gas turbine engine is disclosed. The compressor section includes a vane carrier () adapted to hold ring segment assemblies () that provide optimized blade tip gaps () during a variety of operating conditions. The ring segment assemblies include backing elements () and tip-facing elements () urged into a preferred orientation by biasing elements () that maintain contact along engagement surfaces (). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (), resulting in blade tip gaps that are dynamically adjusted operation.