David P Hanson

US Patent:

20130099944, Apr 25, 2013

Filed:

Oct 19, 2011

Appl. No.:

13/277002

Inventors:

David Richard Hanson - Tempe AZ, US
Dave Dischinger - Tempe AZ, US
Ronald Goodwin - Mesa AZ, US
John Repp - Gilbert AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

G08B 21/00
F02G 3/00

US Classification:

340962, 60 39093

Abstract:

An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports. A processing module is coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.

US Patent:

49029037, Feb 20, 1990

Filed:

Oct 27, 1988

Appl. No.:

7/263652

Inventors:

Eugene E. Segerson - Tempe AZ
David L. Vowles - Phoenix AZ
David D. Hanson - Scottsdale AZ

International Classification:

G01N 2186

US Classification:

250561

Abstract:

An improved vehicle height sensor and automotive leveling system are described using, in a preferred embodiment, two optical emitter-receiver pairs mounted in the sidewall or dust cover of a standard automotive air shock. The emitter-receiver pairs are arranged to operate by reflecting light from the central shaft of the shock absorber. Each emitter-receiver pair provides a light path that lies in a plane substantially perpendicular to the extension direction of the shock. The two emitter receiver pairs are spaced apart along the extension direction of the shock. Movement of the internal piston of the shock successively interrupts (by absorption) the light paths of the emitter-receiver pairs so as to provide a positive indication of the location of the movable piston and hence the height of the shock and the height of vehicle body above the road. The emitter-receiver pairs are mounted in a common assembly and seal to the shock dust cover through a single hole. They are convenient to manufacture in a single module which includes the control logic needed to add to remove fluid from the shock to maintain it in reference position independent of the vehicle load.

US Patent:

20200308970, Oct 1, 2020

Filed:

Mar 25, 2019

Appl. No.:

16/363117

Inventors:

- Morris Plains NJ, US
John Repp - Gilbert AZ, US
David Richard Hanson - Tempe AZ, US
Nick Nolcheff - Chandler AZ, US
Darrell K. James - Cave Creek AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ

International Classification:

F01D 9/04

Abstract:

A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.

US Patent:

20200158127, May 21, 2020

Filed:

Nov 21, 2018

Appl. No.:

16/198266

Inventors:

- Morris Plains NJ, US
Jeffrey Hayes - Apache Junction AZ, US
John A. Gunaraj - Chandler AZ, US
Yoseph Gebre-Giorgis - Phoenix AZ, US
David Richard Hanson - Tempe AZ, US
John Repp - Gilbert AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ

International Classification:

F04D 29/38

Abstract:

A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.

US Patent:

20180355791, Dec 13, 2018

Filed:

Aug 6, 2018

Appl. No.:

16/056101

Inventors:

- Morris Plains NJ, US
John Repp - Gilbert AZ, US
Bruce David Reynolds - Chandler AZ, US
David Richard Hanson - Tempe AZ, US

Assignee:

Honeywell International Inc. - Morris Plains NJ

International Classification:

F02C 3/08
F04D 19/02
F04D 17/02
F04D 29/32
F04D 29/54
F04D 29/28

Abstract:

Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

US Patent:

20170276070, Sep 28, 2017

Filed:

Mar 24, 2016

Appl. No.:

15/079538

Inventors:

- Morris Plains NJ, US
John Repp - Gilbert AZ, US
Bruce David Reynolds - Chandler AZ, US
David Richard Hanson - Tempe AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ

International Classification:

F02C 3/08
F04D 29/54
F04D 29/32
F04D 17/02
F04D 29/28

Abstract:

Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

US Patent:

20160252098, Sep 1, 2016

Filed:

Feb 26, 2015

Appl. No.:

14/632024

Inventors:

- Morristown NJ, US
David Richard Hanson - Tempe AZ, US
John Repp - Gilbert AZ, US
Michael Todd Barton - Phoenix AZ, US
John A. Gunaraj - Chandler AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F04D 27/00
F04D 29/32
F04D 29/54
F04D 19/02

Abstract:

Methods and apparatuses are provided for a compressor. The compressor includes a first stage having a first rotor and a first stator, and a second stage downstream from the first stage in a direction of a fluid flow. The compressor also includes a secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.