David L Wasdell

US Patent:

20130224009, Aug 29, 2013

Filed:

Feb 29, 2012

Appl. No.:

13/408147

Inventors:

David A. Little - Chuluota FL, US
Gerard McQuiggan - Orlando FL, US
David L. Wasdell - Winter Park FL, US

International Classification:

F01D 1/04
F01D 25/00

US Classification:

4152081

Abstract:

A midframe portion () of a gas turbine engine () is presented, and includes a compressor section () configured to discharge an air flow () directed in a radial direction from an outlet of the compressor section (). Additionally, the midframe portion () includes a manifold () to directly couple the air flow () from the compressor section () outlet to an inlet of a respective combustor head () of the midframe portion ().

US Patent:

20120301276, Nov 29, 2012

Filed:

May 23, 2011

Appl. No.:

13/113351

Inventors:

Ram Bahadur Singh - Dist - Alwar, IN
David L. Wasdell - Winter Park FL, US
Keith A Miller - Oviedo FL, US

International Classification:

F01D 25/00

US Classification:

415118

Abstract:

A wear indication system for use in turbine engines to measure the rate of gap closure between a seal holder and a rotor disk in a compressor blade assembly is disclosed. The wear indication system may include a support system capable of supporting a wear indicator formed from a relatively soft wear material without enabling the wear indicator to shift position or to fall out. One or more wear pins may be releasably attached to a compression plate with a seal holder. The seal holder may restrain the wear pin in position in an interference fit. During turbine engine operation, the wear pin is used to determine the rate of gap closing between a rotor disk and a seal holder precisely so that gas turbine engine repair can be scheduled and proper actions be taken to prevent rubbing between rotating and stationary parts of a compressor.

US Patent:

20160376929, Dec 29, 2016

Filed:

Jun 29, 2015

Appl. No.:

14/753384

Inventors:

- Orlando FL, US
Jose L. Rodriguez - Lake Mary FL, US
David L. Wasdell - Winter Park FL, US
John A. Orosa - Palm Beach Gardens FL, US
Matthew D. Montgomery - Jupiter FL, US

International Classification:

F01D 25/30
F01D 25/04
F02C 7/20

Abstract:

An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.