Donald Charles Palmer

US Patent:

6931859, Aug 23, 2005

Filed:

Dec 17, 2003

Appl. No.:

10/739754

Inventors:

Peter L. Morgan - Tempe AZ, US
William J. Howe - Chandler AZ, US
Mark C. Morris - Phoenix AZ, US
Adrian R. Allan - Chandler AZ, US
Donald L. Palmer - Cave Creek AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C007/12

US Classification:

60782, 60785, 137494

Abstract:

Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.

US Patent:

7189059, Mar 13, 2007

Filed:

Oct 27, 2004

Appl. No.:

10/976934

Inventors:

Michael T. Barton - Scottsdale AZ, US
Donald L. Palmer - Cave Creek AZ, US
Mahmoud L. Mansour - Phoenix AZ, US
Don F. Durschmidt - Chandler AZ, US
John A. Gunaraj - Chandler AZ, US
Mark D. Matwey - Phoenix AZ, US
John A. Slovisky - Chandler AZ, US
Nick A. Nolcheff - Phoenix AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F04D 29/44

US Classification:

415186, 415191

Abstract:

A compressor includes an enhanced vaned shroud and is configured such that the flow area ratio is equivalent to that of a conventional, non-vaned shroud. The vaned shroud includes a plurality of airfoils that vary in thickness to obtain desired vibrational mode shapes and natural frequencies. A stiffening ring of limited axial extent is coupled to, and between, the airfoils, and the shroud is manufactured with a section of constant radius.

US Patent:

7717672, May 18, 2010

Filed:

Aug 29, 2006

Appl. No.:

11/512559

Inventors:

Michael T. Barton - Phoenix AZ, US
Harry L. Kington - Scottsdale AZ, US
Donald L. Palmer - Cave Creek AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F01D 9/04

US Classification:

4152082, 4152112

Abstract:

A radial diffuser comprises a housing, a plurality of diffuser vanes, and a plurality of integral service vanes. The housing includes an air inlet and an air outlet, and defines a radial section extending radially outward from the air inlet, an axial section extending axially to the air outlet, and a transition including a bend and extending between the radial and axial sections. The diffuser vanes are coupled to the housing, and are disposed in, and define diffusion flow passages. The integral service vanes are coupled to the housing, extend around the bend, and define transition flow passages, each in fluid communication with at least one diffusion flow passage. At least some of the integral service vanes include a service passage extending therethrough and configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.

US Patent:

8122724, Feb 28, 2012

Filed:

Aug 31, 2004

Appl. No.:

10/931502

Inventors:

John A. Slovisky - Chandler AZ, US
Michael T. Barton - Scottsdale AZ, US
John A. Gunaraj - Chandler AZ, US
Mahmoud L. Mansour - Phoenix AZ, US
Donald L. Palmer - Cave Creek AZ, US
Charles J. Paine - Tempe AZ, US
George L. Perrone - Phoenix AZ, US
Nick A. Nolcheff - Chandler AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F02C 1/00

US Classification:

60772, 60240

Abstract:

A compressor includes a diffuser, a recirculation duct, and a flow control valve. The recirculation duct has an inlet in fluid communication with the air outlet of the diffuser, and an outlet in fluid communication with the air inlet of the diffuser. The flow control valve is selectively moveable between open and closed positions, to thereby fluidly couple and isolate, respectively, the recirculation duct inlet and outlets. During operation of the compressor, the flow control valve may be opened, which circulates a portion of the compressed air discharged from the diffuser air outlet back to the diffuser air inlet. The air that is circulated back to the diffuser air inlet reduces the effective area of the diffuser air inlet, thereby increasing the surge margin of the compressor.

US Patent:

52775410, Jan 11, 1994

Filed:

Dec 23, 1991

Appl. No.:

7/813241

Inventors:

Donald L. Palmer - Cave Creek AZ

Assignee:

Allied-Signal Inc. - Morris Township, Morris County NJ

International Classification:

F01D 504

US Classification:

415 582

Abstract:

A centrifugal compressor impeller for gas turbine engines designed to efficiently operate at both part-speed and full speed design points includes slanted vanes in a secondary air inlet to the impeller. The vanes are tangentially slanted in the direction of rotation of the impeller to preferentially augment airflow into the impeller at maximum speed, while at part-speed discouraging airflow out of its impeller through the secondary inlet.

US Patent:

52363015, Aug 17, 1993

Filed:

Dec 23, 1991

Appl. No.:

7/812674

Inventors:

Donald L. Palmer - Cave Creek AZ

Assignee:

Allied-Signal Inc. - Morris Township, Morris County NJ

International Classification:

F04D 2944

US Classification:

415116

Abstract:

An improved centrifugal compressor for use in gas turbine engines includes a secondary air flow inlet in the compressor shroud at a location downstream of the inducer, with passive elements in the secondary air inlet for effectively preventing flow out of the secondary air inlet from the compressor impeller at part speed design operation, while augmenting and enhancing flow of secondary air flow into the compressor impeller at maximum design speed operation of the compressor impeller.

US Patent:

44702566, Sep 11, 1984

Filed:

Dec 22, 1981

Appl. No.:

6/333500

Inventors:

Donald L. Palmer - Cave Creek AZ

Assignee:

The Garrett Corporation - Los Angeles CA

International Classification:

F02C 900

US Classification:

60 3929

Abstract:

A fluid compressor including a rotating impeller and apparatus inhibiting fluid surging. The surge inhibiting apparatus includes a multitude of guide vanes circumscribing an inlet of the compressor. Movement of the guide vanes with respect to fluid flowing to the compressor is effective to inhibit fluid surging. A combustion turbine including such a fluid compressor, and a vehicle powered by such an engine are also disclosed.

US Patent:

56198507, Apr 15, 1997

Filed:

May 9, 1995

Appl. No.:

8/438145

Inventors:

Donald L. Palmer - Cave Creek AZ
Gulshan K. Arora - Chandler AZ

Assignee:

AlliedSignal Inc. - Morris Township NJ

International Classification:

F02C 718

US Classification:

60 3902

Abstract:

A bleed air buffer seal arrangement is provided for improved buffer sealing of oil sump seals in a gas turbine engine. In a multiple spool gas turbine engine, bleed air for buffer sealing is obtained through an annular bleed slot or annular array of bleed ports formed in the impeller shroud of a high pressure centrifugal impeller at a location spaced aft or downstream from the leading edge thereof. Bleed air from this location exhibits significant pressure at low engine power conditions to provide satisfactory buffer sealing, without subjecting sump seals to excess pressure or temperature at high engine power conditions.