David A Welch

US Patent:

7435050, Oct 14, 2008

Filed:

Jan 11, 2006

Appl. No.:

11/329554

Inventors:

David A. Welch - Quaker Hill CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/40
F01D 25/24

US Classification:

4152141, 415201

Abstract:

There is provided a turbine engine component, such as a duct pipe, comprising an annular flange, at least one element, such as two duct pipe halfs, to be mated to the flange, and mating system for joining the at least one element to the flange. The mating system includes a first annular groove in the flange, which groove has two opposed planar wall portions for preventing axial movement of the at least one element relative to the flange. In a preferred embodiment, the mating system also includes a second annular groove in the flange. A sealing element is positioned within the second annular groove.

US Patent:

8292592, Oct 23, 2012

Filed:

Apr 2, 2008

Appl. No.:

12/080383

Inventors:

David A. Welch - Quaker Hill CT, US
Phillip Alexander - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 11/14

US Classification:

416245R, 415201

Abstract:

A device includes a resilient member having a first end for blocking an access hole and a second end for attachment to a support surface, an opening extending through the resilient member and located between the first and second ends, and a bolt connection location positioned at the second end of the resilient member. The first end of the resilient member blocks the access hole and can be deflected to provide tool access to the bolt connection location through the first opening.

US Patent:

20210404343, Dec 30, 2021

Filed:

Sep 9, 2021

Appl. No.:

17/470638

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F01D 5/14
B29C 64/153
B22F 5/04
B23K 26/34
B23P 15/04
F04D 29/32

Abstract:

A blade fabrication method is provided and includes additively manufacturing a core, securing the core to a mandrel, electroforming a leading edge sheath directly onto the core and the mandrel and removing the mandrel from the core and the leading edge sheath.

US Patent:

20200173286, Jun 4, 2020

Filed:

Dec 4, 2018

Appl. No.:

16/209448

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F01D 5/14
F04D 29/32
B23P 15/04
B22F 5/04
B29C 64/153
B23K 26/34

Abstract:

A blade fabrication method is provided and includes additively manufacturing a core, securing the core to a mandrel, electroforming a leading edge sheath directly onto the core and the mandrel and removing the mandrel from the core and the leading edge sheath.

US Patent:

20180073519, Mar 15, 2018

Filed:

Sep 14, 2016

Appl. No.:

15/265294

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F04D 29/38

Abstract:

An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.

US Patent:

20180038385, Feb 8, 2018

Filed:

Aug 2, 2016

Appl. No.:

15/226147

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F04D 29/38
F04D 19/00
B22F 5/04
F04D 29/02
B22F 3/105
F02K 3/06
F04D 29/32

Abstract:

A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.

US Patent:

20170298821, Oct 19, 2017

Filed:

Apr 18, 2016

Appl. No.:

15/131145

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F02C 7/047
F02C 7/24
F02C 7/30

Abstract:

A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed.

US Patent:

20170284202, Oct 5, 2017

Filed:

Apr 5, 2016

Appl. No.:

15/091066

Inventors:

- Farmington CT, US
David A. Welch - Quaker Hill CT, US

International Classification:

F01D 5/00
F01D 5/32
F02K 3/06
F01D 5/02
F01D 25/24
F01D 5/30
F02C 3/04

Abstract:

A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.