Eric R Grover

US Patent:

7686567, Mar 30, 2010

Filed:

Dec 16, 2005

Appl. No.:

11/303672

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 27/02

US Classification:

415 1, 415191, 416223 R, 416243, 416DIG 2

Abstract:

A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.

US Patent:

7887297, Feb 15, 2011

Filed:

May 2, 2006

Appl. No.:

11/415915

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US
Joel H. Wagner - Wethersfield CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/22

US Classification:

416193A

Abstract:

An airfoil array includes a laterally extending endwall with a series of airfoils such as , or projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages. The endwall has a hump toward a pressure side of the passage and a less elevated profile toward a suction side of the passage for reducing secondary flow losses.

US Patent:

8105037, Jan 31, 2012

Filed:

Apr 6, 2009

Appl. No.:

12/418647

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US
Renee J. Jurek - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/44

US Classification:

416193A, 416179

Abstract:

An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped area forward the airfoil leading edge portion.

US Patent:

8240121, Aug 14, 2012

Filed:

Nov 20, 2007

Appl. No.:

11/942962

Inventors:

Robert L. Hazzard - Windsor CT, US
Joel H. Wagner - Wethersfield CT, US
Edward M. Henrahan - South Windsor CT, US
Ryan Shepard Levy - Middletown CT, US
Takao Fukuda - Wethersfield CT, US
Eric A. Grover - Tolland CT, US
Paul Smith - Glastonbury CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02G 3/00

US Classification:

60 39092, 60796, 55306, 55511, 4151212, 2988902

Abstract:

A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.

US Patent:

8356975, Jan 22, 2013

Filed:

Mar 23, 2010

Appl. No.:

12/730191

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/44
F04D 29/54
F03B 1/00
F03B 11/02
F03D 5/00

US Classification:

415191, 4152112

Abstract:

A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.

US Patent:

8366399, Feb 5, 2013

Filed:

May 2, 2006

Appl. No.:

11/415892

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/38
F04D 29/00

US Classification:

416228, 416234

Abstract:

A blade or vane includes a platform and an airfoil extending from the platform. The airfoil has a pressure surface offset in a first direction D from a part span mean camber line , a suction surface offset in a second direction D from the part span mean camber line, and a base that is laterally enlarged in the first direction for reducing secondary flow losses.

US Patent:

8511978, Aug 20, 2013

Filed:

May 2, 2006

Appl. No.:

11/415898

Inventors:

Eric A. Grover - Tolland CT, US
Thomas J. Praisner - Colchester CT, US
Joel H. Wagner - Wethersfield CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 1/04
F01D 9/02

US Classification:

415191, 416193 A

Abstract:

An airfoil array includes a laterally extending endwall with a series of airfoils such as or projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages. The endwall has a trough toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.

US Patent:

20110243749, Oct 6, 2011

Filed:

Apr 2, 2010

Appl. No.:

12/753211

Inventors:

Thomas J. Praisner - Tolland CT, US
Eric A. Grover - Tolland CT, US

International Classification:

F01D 5/14

US Classification:

416223 A

Abstract:

A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.