39 patents
Utility
Gas turbine engine with active clearance control
14 Nov 23
A small gas turbine engine, such as is used to power a UAV, that includes at least one centrifugal compressor having an impeller with blades that form a gap between the blade tips and stationary shroud of the gas turbine engine, and where a resistance heating element, such as an impingement air manifold, is secured to or bonded to a compressor casing of the gas turbine engine in order to use heat to control the gap between the impeller blades and the stationary shroud.
Robert A. Ress, Jr.
Filed: 22 Oct 21
Utility
Physically unclonable functions using pulse width chaotic maps
7 Nov 23
Technologies are provided for clockless physically unclonable functions (PUFs) in reconfigurable devices.
Seth D. Cohen
Filed: 10 Jan 22
Utility
Target ranging with subsampled noise correlation
22 Aug 23
Backend components for noise radar and techniques for operation of those components are provided.
Seth D. Cohen, Aubrey Beal
Filed: 21 May 21
Utility
Clockless time-to-digital converter
15 Aug 23
Technologies are provided for time-to-digital conversion without reliance on a clocking signal.
Seth D. Cohen
Filed: 6 Jul 22
Utility
2D variable-area plug nozzle
30 May 23
A two-dimensional variable area plug (2D VAP) nozzle assembly for a high-speed flight vehicle.
Robert A. Ress, Jr.
Filed: 17 Jan 22
Utility
Contactless Vital Sign Monitoring of Multiple Subjects In Real-time
25 May 23
Systems and methods are provided to monitor vital signs from a plurality of subjects simultaneously and in real-time.
Seth Daniel Cohan, Stacey Suzanne Kelpke, Jacob Matthew Robinson
Filed: 6 Apr 21
Utility
Clockless Time-to-digital Converter
5 Jan 23
Technologies are provided for time-to-digital conversion without reliance on a clocking signal.
Seth D. Cohen
Filed: 6 Jul 22
Utility
Clockless time-to-digital converter
16 Aug 22
Technologies are provided for time-to-digital conversion without reliance on a clocking signal.
Seth D. Cohen
Filed: 10 Jun 19
Utility
Deployable power pack for a dual mode high speed propulsion system
26 Apr 22
An aero vehicle with a dual mode propulsion system that can operate in a first mode below a ramjet speed and a second mode at a ramjet speed.
Robert A Ress, Jr., Joseph D Brostmeyer
Filed: 9 Jul 19
Utility
Multi-spool geared turbofan arrangement with integrated starter/generator
29 Mar 22
A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator.
Joseph D. Brostmeyer, Robert A. Ress, Jr., Tyler W. Sloss, Barry J. Brown
Filed: 22 Jun 20
Utility
Aero gas turbine engine with speed reduction gearbox
22 Mar 22
A lay shaft assembly for a speed reduction gearbox in a geared turbofan gas turbine engine, the lay shaft assembly having an output gear formed on a lay shaft as a single piece, and an input welded gear formed as a separate piece that is welded to the shaft in close proximity to the output gear.
Robert A Ress, Jr., Stephen M Brooks
Filed: 11 Aug 19
Utility
Multi-spool Geared Turbofan Arrangement with Integrated Starter/generator
23 Dec 21
A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator.
Joseph D. BROSTMEYER, Robert A. RESS, JR., Tyler W. SLOSS, Barry J. BROWN
Filed: 22 Jun 20
Utility
Gas turbine engine with active clearance control
30 Nov 21
A small gas turbine engine, such as is used to power a UAV, that includes at least one centrifugal compressor having an impeller with blades that form a gap between the blade tips and stationary shroud of the gas turbine engine, and where a resistance heating element is secured to or bonded to a compressor casing of the gas turbine engine in order to use heat to control the gap between the impeller blades and the stationary shroud.
Robert A. Ress, Jr.
Filed: 20 May 21
Utility
Apparatus and process for testing a large combustor using a CAES facility
30 Nov 21
An apparatus, system, and process for testing a gas turbine engine or other test object under a cold condition, such as a compressor of a gas turbine engine, a combustor of a gas turbine engine, or an afterburner of an aero gas turbine engine, using compressed air stored in an underground storage reservoir of a CAES system along with an air turbine or an air injector.
Joseph D. Brostmeyer, Scott A. Baker
Filed: 18 Sep 17
Utility
Gas turbine engine bearing with fuel lubrication and cooling
23 Nov 21
A gas turbine engine with a bearing that is supplied with fuel and compressed air for both cooling and lubrication of the bearing.
Robert A Ress, Jr., Brian E Taylor
Filed: 28 Feb 19
Utility
High speed shaft flexible coupling
23 Nov 21
A gas turbine engine in which a long length-to-diameter (L/D) flexible shaft is used to connect two high speed shafts in order to tolerate misalignment.
Stephen M Brooks, Alex Pinera
Filed: 10 Sep 19
Utility
Group Iva Functionalized Particles and Methods of Use Thereof
11 Nov 21
Disclosed are functionalized Group IVA particles, methods of preparing the Group IVA particles, and methods of using the Group IVA particles.
Timothy D. Newbound, Leslie Matthews, Jeff A. Norris
Filed: 22 Apr 21
Utility
Process of forming a metal additive manufactured part with a smooth surface
21 Sep 21
A process for forming a metal part from an additive manufacturing process with a smooth surface that includes the steps of printing the part using an AM process, heating the printed part to its solution heat treat or annealing temperature, placing the printed part in a fluidized salt bath for a short period of time to smooth a rough surface on the metal part, and then rapidly cool the heated metal part to prevent any change in grain structure.
Alex Pinera
Filed: 21 Jun 18
Utility
Industrial Gas Turbine Engine with First and Second Stage Rotor Cooling
8 Jul 21
An industrial gas turbine engine with first and stage turbine rotor blade cooling circuit in which the blade cooling air flows through a central passage within the rotor of the engine, flows through a space between first and second stage rotors, separates into two flows with one flow going to the first stage blades and the second flow going to the second stage blades, the two flows then collecting in a common manifold, where the spent blade cooling air flows forward through the first stage rotor and along a rotor cooling passage and into a stator cavity, where the cooling air then is discharged into a combustor.
Russel B. JONES, Wesley D. BROWN
Filed: 14 Feb 17
Utility
Process for retrofitting an industrial gas turbine engine for increased power and efficiency
22 Jun 21
A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor.
Russell B. Jones, Joseph D. Brostmeyer, Justin T. Cejka, John E. Ryznic
Filed: 15 May 17