Jeffrey D Clements

US Patent:

6398487, Jun 4, 2002

Filed:

Jul 14, 2000

Appl. No.:

09/616257

Inventors:

Thomas Tracy Wallace - Maineville OH
Christopher Charles Glynn - Hamilton OH
Monty Lee Shelton - Loveland OH
Jeffrey Donald Clements - Mason OH
Dean Thomas Lenahan - Cincinnati OH
Barry John Kalb - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 514

US Classification:

415115, 415191, 415202, 4152082

Abstract:

A gas turbine engine rotor assembly includes a plurality of aerodynamic devices to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft that includes a plurality of openings. The aerodynamic devices include a pair of vane segments and a pair of sidewalls. A contoured outer surface includes an opening and permits the aerodynamic device to be positioned against an inner surface of the rotor shaft, and a flange ring defines a pocket. The aerodynamic device fits within the pocket to concentrically align the openings.

US Patent:

8459956, Jun 11, 2013

Filed:

Dec 24, 2008

Appl. No.:

12/344058

Inventors:

Vidhu Shekhar Pandey - West Chester OH, US
Jan Christopher Schilling - Middletown OH, US
Aspi Rustom Wadia - Loveland OH, US
Brian David Keith - Cincinnati OH, US
Jeffrey Donald Clements - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/14

US Classification:

416243, 416223 R, 416193 A, 416193 R, 416190, 416192

Abstract:

A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.

US Patent:

8647067, Feb 11, 2014

Filed:

Dec 9, 2008

Appl. No.:

12/330783

Inventors:

Vidhu Shekhar Pandey - West Chester OH, US
Jeffrey Donald Clements - Mason OH, US

Assignee:

General Electric company - Schenectady NY

International Classification:

B63H 1/26
B63H 1/16

US Classification:

416223R, 416193 A, 416193 R

Abstract:

A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.

US Patent:

20120051894, Mar 1, 2012

Filed:

Aug 31, 2010

Appl. No.:

12/872770

Inventors:

Jeffrey Donald Clements - Mason OH, US
Vidhu Shekhar Pandey - West Chester OH, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F04D 29/44

US Classification:

415191

Abstract:

A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.

US Patent:

20120051930, Mar 1, 2012

Filed:

Aug 31, 2010

Appl. No.:

12/872827

Inventors:

Vidhu Shekhar Pandey - West Chester OH, US
Aspi Rustom Wadia - Loveland OH, US
Jeffrey Donald Clements - Mason OH, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F04D 29/38

US Classification:

416223 A

Abstract:

A turbine blade includes an airfoil having a root, a tip, a concave pressure side, and a laterally opposite convex suction side, the pressure and suction sides extending in chord between opposite leading and trailing edges; an outer platform disposed at the tip of the airfoil, the outer platform having spaced-apart lateral edges which each define an interlocking element; an inner platform with two spaced-apart curved lateral edges disposed at the root of the airfoil, the inner platform having a hot side facing the airfoil which is contoured in a non-axisymmetric shape; and a dovetail extending radially inward from the opposite side of the inner platform, wherein the dovetail is axially straight.

US Patent:

6361277, Mar 26, 2002

Filed:

Jan 24, 2000

Appl. No.:

09/490625

Inventors:

David E. Bulman - Cincinnati OH
Kenneth E. Seitzer - Mason OH
Craig P. Burns - Mason OH
Jeffrey D. Clements - Mason OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 508

US Classification:

416 96R, 416198 A

Abstract:

A gas turbine engine includes a compressor rotor assembly which directs air at a sufficent pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor including a plurality of rotors joined with a plurality of couplings. Each of the rotors includes a radially outer rim, a radially inner hub, and a web extending therebetween. The web includes a flange including a plurality of slots which define a plurality of radial vanes that are airfoil-shaped. The vanes effectively deswirl bleed air and re-direct the airflow to a compressor bore.

US Patent:

20220403799, Dec 22, 2022

Filed:

Aug 22, 2022

Appl. No.:

17/892549

Inventors:

- Schenectady NY, US
Randy M. Vondrell - Cincinnati OH, US
Jeffrey Donald Clements - Mason OH, US
Brandon Wayne Miller - Liberty Township OH, US

International Classification:

F02K 3/075
F02K 3/06
F02C 7/36
F02C 3/13
F02C 3/107
F02C 7/20
F01D 21/04
B64D 29/02
B64D 27/12

Abstract:

The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a fan assembly including a plurality of fan blades rotatably coupled to a fan rotor in which the fan blades define a maximum fan diameter and a fan pressure ratio. The gas turbine engine further includes a low pressure (LP) turbine defining a core flowpath therethrough generally along the longitudinal direction. The core flowpath defines a maximum outer flowpath diameter relative to the axial centerline. The gas turbine engine defines a fan to turbine diameter ratio of the maximum fan diameter to the maximum outer flowpath diameter. The fan to turbine diameter ratio over the fan pressure ratio is approximately 0.90 or greater.

US Patent:

20220259985, Aug 18, 2022

Filed:

Feb 15, 2021

Appl. No.:

17/176106

Inventors:

- Schenectady NY, US
Trevor Goerig - Mt. Healthy OH, US
Jeffrey D. Clements - Mason OH, US
Syed Arif Khalid - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 15/12
F02C 6/20

Abstract:

A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ftat a takeoff flight condition.