David A Knaul

US Patent:

20130259659, Oct 3, 2013

Filed:

Mar 27, 2012

Appl. No.:

13/430929

Inventors:

David A. Knaul - Glastonbury CT, US
Fadi S. Maalouf - East Hampton CT, US
Nicholas Aiello - New Haven CT, US
Orenthral T. Morgan - East Hartford CT, US
Raji Mali - Shelton CT, US

Assignee:

Pratt & Whitney - East Hartford CT

International Classification:

F04D 29/08

US Classification:

4151701

Abstract:

A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.

US Patent:

20090297350, Dec 3, 2009

Filed:

May 30, 2008

Appl. No.:

12/129799

Inventors:

Scott J. Augustine - Wethersfield CT, US
David A. Knaul - Glastonbury CT, US

International Classification:

F01D 5/22
F02C 7/18

US Classification:

416192, 415115

Abstract:

A mount interface between two rotating gas turbine engine components includes a rigid ring to provide radial deflection restraint. In one example, the rigid ring is comprised of a metal matrix composite material.

US Patent:

20210277829, Sep 9, 2021

Filed:

Apr 30, 2020

Appl. No.:

16/863218

Inventors:

- Farmington CT, US
Anthony R. Bifulco - Ellington CT, US
David A. Topol - West Hartford CT, US
David A. Knaul - Glastonbury CT, US
Michael Raymond LaFavor - Manchester CT, US

International Classification:

F02C 7/24
F04D 29/66

Abstract:

Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.

US Patent:

20160319835, Nov 3, 2016

Filed:

Dec 10, 2014

Appl. No.:

15/104251

Inventors:

- Hartford CT, US
David A. KNAUL - Glastonbury CT, US
Michael ESPINOZA - Middletown CT, US

International Classification:

F04D 29/32
F01D 5/02
F01D 5/34

Abstract:

An integrally bladed rotor includes a rotor that has a rim that provides an inner flow surface. Circumferentially spaced apart radially extending airfoils integrally with and from the rotor and joined by an airfoil fillet. An asymmetrical trench is provided in the rim between adjacent airfoils.