David Allen Calta

US Patent:

6634176, Oct 21, 2003

Filed:

Oct 15, 2001

Appl. No.:

09/977445

Inventors:

Gregory C. Rouse - Westlake Village CA
Octavio Solis - Los Angeles CA
David Calta - Newbury Park CA

Assignee:

Capstone Turbine Corporation - Chatsworth CA

International Classification:

F02C 314

US Classification:

60804, 60 39511, 60670

Abstract:

In a turbine engine with an annular recuperator surrounding the turbine, exhaust gas is directed from the turbine to the recuperator by a generally curved exhaust dome. A vortex disrupter structure extends from the exhaust dome to a point distal of the turbine to evenly distribute the exhaust gas entering the recuperator and sustain diffusion of the exhaust gas to increase the expansion ratio across the turbine.

US Patent:

7014418, Mar 21, 2006

Filed:

Dec 3, 2004

Appl. No.:

11/004467

Inventors:

Steve Don Arnold - Ranch Palos Verdes CA, US
Kristian N. Dullack - Carson CA, US
David A. Calta - Redondo Beach CA, US
Glenn F. Thompson - Palos Verdes Estates CA, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F01D 25/24

US Classification:

415100, 415204, 415206, 4152112

Abstract:

A multi-stage compressor and associated compressor housing and method are provided. The housing defines an aperture for receiving a compressor wheel for successively compressing a gas in first and second stages. First- and second-stage inlets are fluidly connected to the aperture in generally axial directions, and first- and second-stage volutes extend at least partially annularly therearound so that each volute is configured to receive gas flowing generally radially outward from the compressor wheel. In addition, first and second passages fluidly connect the first-stage volute to the second-stage inlet. Each passage extends from the first-stage volute to a position radially outward of the second-stage volute and therefrom to the second-stage inlet at an axial position opposite the second-stage volute from the first-stage volute. Thus, the gas can be received through the first-stage inlet, compressed by the wheel, circulated to the second-stage inlet via the first-stage volute and the passages, compressed again by the wheel, and delivered to the second-stage volute.

US Patent:

7305827, Dec 11, 2007

Filed:

Nov 22, 2005

Appl. No.:

11/285665

Inventors:

Steve Don Arnold - Ranch Palos Verdes CA, US
David A. Calta - Newbury Park CA, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F02B 33/44

US Classification:

606051

Abstract:

A turbocharger includes a compressor wheel having back-to-back impellers (i. e. , a forward-facing impeller and a rearward-facing impeller) mounted on the same shaft. The two impellers are independently supplied with inlet air via separate inlet ducts and discharge pressurized air to a common volute. The inlet duct for the rearward-facing impeller comprises a generally axially extending tubular conduit having an upstream end and a downstream end, the tubular conduit being bifurcated at the downstream end into a pair of separate duct branches that divide an air stream flowing through the tubular conduit into a pair of separate air streams. The duct branches direct the air streams radially inwardly and then re-join the streams and turn the air to an axial direction into the second impeller.

US Patent:

7407364, Aug 5, 2008

Filed:

Mar 1, 2005

Appl. No.:

11/069336

Inventors:

Steve Don Arnold - Ranch Palos Verdes CA, US
Kristian N. Dullack - Carson CA, US
David A. Calta - Newbury Park CA, US
Glenn F. Thompson - Palos Verdes Estates CA, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F01D 25/26

US Classification:

415 584, 415100, 415144, 4152112

Abstract:

A two-stage radial compressor having a ported second-stage shroud, forming a passive surge control system. Thus, some proportion of the fluid is allowed to flow between the second-stage of the compressor in the vicinity of the impeller blade tips, through a port in the shroud into an upstream portion of the compressor flow path that leads into the second-stage impeller inlet. The fluid is allowed to flow in either direction, depending on the pressure difference existing between the two locations. Surge margin at higher pressure ratios is significantly increased by the ported second-stage shroud.

US Patent:

8511083, Aug 20, 2013

Filed:

Dec 15, 2005

Appl. No.:

11/304376

Inventors:

Steven Don Arnold - Ranch Palos Verdes CA, US
David A. Calta - Newbury Park CA, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F02D 23/00
F02B 33/44

US Classification:

60602, 60598

Abstract:

A turbocharger system having a compressor wheel including blades that define an inducer and an exducer, a compressor housing configured to receive the compressor wheel, and an impeller passage within which air is to be compressed by the blades, wherein the compressor housing forms an intake port configured to provide intake air to the inducer, and a bypass port opening into the impeller passage between the inducer and exducer. The bypass port places the impeller passage in fluid communication with the atmosphere without having a fluid interaction with the intake air. A bypass-air filter is adapted to filter air passing between the bypass port and the atmosphere, and is a portion of the intake-air filter.

US Patent:

20020066270, Jun 6, 2002

Filed:

Nov 6, 2001

Appl. No.:

09/985789

Inventors:

Gregory Rouse - Westlake Village CA, US
Bill Treece - La Mesa CA, US
Jeff Willis - Los Angeles CA, US
David Calta - Newbury Park CA, US

Assignee:

CAPSTONE TURBINE CORPORATION - Chatsworth CA

International Classification:

F01K013/00
F01K001/00

US Classification:

060/670000, 060/645000

Abstract:

A closed loop Rankine bottoming cycle including a heat exchanger coupled to an exhaust port of a first turbogenerator for heating a pressurized refrigerant into a gaseous phase, and a second turbogenerator (e.g., a turbo expander) coupled to the heat exchanger for expanding the gaseous phase so as to create power. Also included is a cooling mechanism coupled to an exhaust of the second turbogenerator for cooling the gaseous phase exhausted by the second turbogenerator into a liquid phase, and a pumping mechanism for pressurizing the liquid phase into the pressurized refrigerant heated by the heat exchanger. A computer program product and method for operating and synchronizing the generator included in the closed loop, so as to optimize the overall system efficiency is also included.

US Patent:

20030110773, Jun 19, 2003

Filed:

Feb 4, 2003

Appl. No.:

10/358060

Inventors:

Gregory Rouse - Westlake Village CA, US
Bill Treece - La Mesa CA, US
Jeff Willis - Los Angeles CA, US
David Calta - Newbury Park CA, US

Assignee:

Capstone Turbine Corporation

International Classification:

F01K001/00
F01K013/00

US Classification:

060/670000, 060/676000

Abstract:

A closed loop Rankine bottoming cycle including a heat exchanger coupled to an exhaust port of a first turbogenerator for heating a pressurized refrigerant into a gaseous phase, and a second turbogenerator (e.g., a turbo expander) coupled to the heat exchanger for expanding the gaseous phase so as to create power. Also included is a cooling mechanism coupled to an exhaust of the second turbogenerator for cooling the gaseous phase exhausted by the second turbogenerator into a liquid phase, and a pumping mechanism for pressurizing the liquid phase into the pressurized refrigerant heated by the heat exchanger. A computer program product and method for operating and synchronizing the generator included in the closed loop, so as to optimize the overall system efficiency is also included.