Matthew T Lang

US Patent:

20210308809, Oct 7, 2021

Filed:

May 1, 2018

Appl. No.:

17/051468

Inventors:

- Orlando FL, US
Matthew H. Lang - Orlando FL, US

International Classification:

B23K 35/30

Abstract:

A weld filler is proposed which significantly improves the weldability of some nickel-based superalloys and includes the following constituents (in wt %): 11.2%-15.6% chromium (Cr), 9.6%-11.4% cobalt (Co) 2.4%-5.0%, molybdenum (Mo) 0.1%-3.3%, 4.4%-7.5% tungsten (W), 1.4%-2.6% tantalum (Ta), 3.0%-4.8% aluminum (Al), 0.4-1.0% titanium (Ti), 0.07%-0.08% carbon (C), 0.5%-1.4% hafnium (Hf), trace elements, and remainder nickel. A method is also provided. The method includes providing a nickel-based substrate to weld, applying a ductile weld filler having a closely matched coefficient of thermal expansion to a surface of the substrate, applying heat to melt the weld filler to form molten weld filler, welding the substrate with the weld filler at ambient temperature, and resolidifying the molten weld filler to form a solidified joint material.

US Patent:

20200392865, Dec 17, 2020

Filed:

Dec 1, 2017

Appl. No.:

16/767133

Inventors:

- Orlando FL, US
Veronica Arocho Pettit - Winter Springs FL, US
Matthew H. Lang - Orlando FL, US
Andrew Medla - Oviedo FL, US

International Classification:

F01D 25/12
F01D 5/18

Abstract:

A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.

US Patent:

20170320171, Nov 9, 2017

Filed:

Apr 24, 2017

Appl. No.:

15/495005

Inventors:

- Orlando FL, US
GERALD J. LYNCH - WINSTON-SALEM NC, US
MATTHEW H. LANG - ORLANDO FL, US

International Classification:

B23K 35/36
B23K 26/24
B23K 26/211
B23K 26/12
B23K 35/362
B23K 26/32

Abstract:

A method of welding including: applying a flux having at least a majority weight percent boron to a surface of a superalloy base material; forming a weldment on the surface wherein boron is melted onto the surface and is incorporated into a resulting weld pool and heat affected zone, and wherein incipient melted inter-dendritic material resulting from presence of the boron is available to flow into a crack formed during cooling of the weldment; and heat treating the weldment to diffuse a remaining concentration of the boron in the weldment and heat affected zone to a desired value.

US Patent:

20160305278, Oct 20, 2016

Filed:

Apr 15, 2015

Appl. No.:

14/687052

Inventors:

- Orlando FL, US
Matthew H. Lang - Orlando FL, US

International Classification:

F01D 25/04
F01D 9/04

Abstract:

A stage () of stationary vanes () of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (); and an energy damping system () having a plurality of connection assemblies (), each joining respective adjacent stationary vanes. A spring () is configured to circumferentially bias respective adjacent stationary vanes, and a damper () is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.

US Patent:

20150118040, Apr 30, 2015

Filed:

Oct 25, 2013

Appl. No.:

14/062925

Inventors:

Ching-Pang Lee - Cincinnati OH, US
Mrinal Munshi - Orlando FL, US
Adam C. Pela - Jupiter FL, US
Paul Bradley Davis - Stuart FL, US
Matthew H. Lang - Orlando FL, US

International Classification:

F01D 9/04

US Classification:

4152093

Abstract:

A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.