Charles C Cornelius

US Patent:

7044017, May 16, 2006

Filed:

Jun 9, 2003

Appl. No.:

10/458050

Inventors:

Charles C. Cornelius - Kirkland WA, US
Shawn P. Lawlor - Bellevue WA, US

International Classification:

F16H 1/18
F16H 1/20

US Classification:

7442488, 7442481, 7442482, 7442492

Abstract:

A higher efficiency roller screw system that includes a nut body designed to engage a threaded shaft. The nut body includes a center bore with closed, partial helical grooves formed therein. Disposed inside the center bore is a shaft with open helical threads formed thereon. A plurality of rollers with non-helical grooves formed thereon are also disposed inside the nut body's center bore and longitudinally aligned with the shaft. The grooves on each roller are designed to engage the grooves on the nut body and the threads on the shaft. The nut body includes a cross-over region where the trajectory of the internal grooves extend radially outward and axially. When the rollers' grooves contact the grooves in the cross-over region, the rollers are forced outward to maintain contact with the grooves on the nut body and are deflected axially. When they move outward, they disengage from the helical threads on the shaft. As the nut body continues to rotate, the grooves on the rollers maintain contact with the grooves on the nut body and re-engage the helical threads on the shaft.

US Patent:

7293955, Nov 13, 2007

Filed:

Mar 23, 2005

Appl. No.:

11/087336

Inventors:

Shawn P. Lawlor - Bellevue WA, US
Mark A. Novaresi - San Diego CA, US
Charles C. Cornelius - Kirkland WA, US

Assignee:

Ramgen Power Systrms, Inc. - Bellevue WA

International Classification:

F01D 1/34

US Classification:

415 90, 415 73, 415 99, 415102, 415144, 415151, 415191, 416199, 416198

Abstract:

A gas compressor based on the use of a driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by the use of a pre-swirl compressor, and using a bypass stream to bleed a portion of the intermediate pressure gas after passing through the pre-swirl compressor back to the inlet of the pre-swirl compressor. Inlet guide vanes to the compression ramp enhance overall efficiency.

US Patent:

7334990, Feb 26, 2008

Filed:

Mar 28, 2005

Appl. No.:

11/091680

Inventors:

Shawn P. Lawlor - Bellevue WA, US
Mark A. Novaresi - San Diego CA, US
Charles C. Cornelius - Kirkland WA, US

Assignee:

Ramgen Power Systems, Inc. - Bellevue WA

International Classification:

B63H 11/00

US Classification:

416 20R, 416 21, 416 22

Abstract:

A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.

US Patent:

7434400, Oct 14, 2008

Filed:

Mar 30, 2005

Appl. No.:

11/102937

Inventors:

Shawn P. Lawlor - Bellevue WA, US
Mark A. Novaresi - San Diego CA, US
Charles C. Cornelius - Kirkland WA, US

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60726, 60772

Abstract:

A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdynamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.

US Patent:

8167534, May 1, 2012

Filed:

Sep 13, 2007

Appl. No.:

11/898639

Inventors:

Charles C. Cornelius - Coronado CA, US
Gabriel J. Glynn - San Diego CA, US

Assignee:

Solar Turbines Inc. - San Diego CA

International Classification:

F01D 11/04

US Classification:

415112, 4151682, 4151684, 4151745, 415230

Abstract:

In one aspect, the present disclosure is directed to a turbine engine. The engine may include a main housing defining a compressor compartment and an air intake housing mounted to the main housing. The engine may also include a rotor including a compressor portion disposed within the compressor compartment, and a hub portion extending from the compressor compartment through an opening in the air intake housing into a bearing compartment defined by the air intake housing. The engine may further include a seal mounted in the opening in the air intake housing in an annular gap between the hub portion of the rotor and the air intake housing and configured to form a seal between the bearing compartment and the compressor compartment. The seal may be configured to be removed from the opening in the air intake housing while the air intake housing is mounted to the main housing.

US Patent:

20030210980, Nov 13, 2003

Filed:

Jan 29, 2003

Appl. No.:

10/355784

Inventors:

Shawn Lawlor - Redmond WA, US
Mark Novaresi - Woodinville WA, US
Charles Cornelius - Kirkland WA, US

Assignee:

RAMGEN POWER SYSTEMS, INC.

International Classification:

F03D001/00

US Classification:

415/001000

Abstract:

A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.

US Patent:

20040151579, Aug 5, 2004

Filed:

Sep 25, 2003

Appl. No.:

10/672719

Inventors:

Shawn Lawlor - Bellevue WA, US
Mark Novaresi - San Diego CA, US
Charles Cornelius - Kirkland WA, US

Assignee:

RAMGEN POWER SYSTEMS, INC.

International Classification:

F04D001/04

US Classification:

415/071000

Abstract:

A gas compressor based on the use of a driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by the use of a pre-swirl compressor, and using a bypass stream to bleed a portion of the intermediate pressure gas after passing through the pre-swirl compressor back to the inlet of the pre-swirl compressor. Inlet guide vanes to the compression ramp enhance overall efficiency.

US Patent:

20040154305, Aug 12, 2004

Filed:

Sep 25, 2003

Appl. No.:

10/672358

Inventors:

Shawn Lawlor - Bellevue WA, US
Mark Novaresi - San Diego CA, US
Charles Cornelius - Kirkland WA, US

Assignee:

RAMGEN POWER SYSTEMS, INC.

International Classification:

F02C001/00

US Classification:

060/772000, 060/726000

Abstract:

A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.