John G Garvey

US Patent:

7829806, Nov 9, 2010

Filed:

Apr 20, 2007

Appl. No.:

11/788776

Inventors:

John C. Garvey - Chicago IL, US

Assignee:

ITT Manufacturing Enterprises, Inc. - Wilmington DE

International Classification:

H01H 35/06

US Classification:

200 819R

Abstract:

The present invention provides a flowswitch for installing in piping, featuring a flowswitch base having an inner cavity; a pivot rod being arranged for rotating in the flowswitch base, the pivot rod having a pair of O-ring grooves; a paddle arm being coupled to the pivot rod inside the cavity, for moving in response to fluid flowing in the piping and rotating the pivot arm; lubricating O-rings being installed onto the pivot rod with each O-ring arranged in a respective O-ring groove for providing a respective seal between fluid being sensed and the outside environment and acting as a bearing on which the pivot rod rotates when the paddle arm moves, the grooves acting to holding the O-rings in place on the pivot arm in response to pressurized fluid flowing in the piping; and an actuating arm being coupled between the pivot arm and the pivot rod for actuating a switch when the pivot arm rotates.

US Patent:

20190063371, Feb 28, 2019

Filed:

Aug 10, 2018

Appl. No.:

16/101000

Inventors:

- Tucson AZ, US
John Garvey - Long Beach CA, US
Christopher Anderson - San Marcos CA, US
Eric Besnard - Long Beach CA, US

Assignee:

Vector Launch Inc. - Tucson AZ

International Classification:

F02K 9/52
B22F 3/105
B33Y 10/00
B22F 3/00
B33Y 80/00
F02K 9/56

Abstract:

Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.

US Patent:

20170096967, Apr 6, 2017

Filed:

Oct 4, 2016

Appl. No.:

15/285324

Inventors:

- Tucson AZ, US
John Garvey - Long Beach CA, US
Christopher Anderson - San Marcos CA, US
Eric Besnard - Long Beach CA, US

International Classification:

F02K 9/52
B33Y 80/00
B22F 3/00
F02K 9/56
B33Y 10/00

Abstract:

Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.