Matthew R 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:

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.