Roger Darrell Walker

US Patent:

6398500, Jun 4, 2002

Filed:

May 24, 2001

Appl. No.:

09/863899

Inventors:

Poul D. Pedersen - Cincinnati OH
Christopher C. Glynn - Hamilton OH
Roger C. Walker - Piedmont SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 532

US Classification:

416220R, 416221, 2988921

Abstract:

A retention system and method for the blades of a rotary machine for preventing forward or aft axial movement of the rotor blades includes a circumferential hub slot formed about a circumference of the machine hub. The rotor blades have machined therein a blade retention slot which is aligned with the circumferential hub slot when the blades are received in correspondingly shaped openings in the hub. At least one ring segment is secured in the blade retention slots and the circumferential hub slot to retain the blades from axial movement. A key assembly is used to secure the ring segments in the aligned slots via a hook portion receiving the ring segments and a threaded portion that is driven radially outwardly by a nut. A cap may be provided to provide a redundant back-up load path for the centrifugal loads on the key. Alternatively, the key assembly may be formed in the blade dovetail.

US Patent:

57137218, Feb 3, 1998

Filed:

May 9, 1996

Appl. No.:

8/644019

Inventors:

Christopher C. Glynn - Hamilton OH
Poul D. Pedersen - Cincinnati OH
Frederick M. Miller - Cincinnati OH
Roger C. Walker - Middletown OH
Sang Yeng Park - West Chester OH
Clifford C. May - Cincinnati OH

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F04D 2934

US Classification:

416220R

Abstract:

One form of a retention system includes a pair of aft segments of 180. degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30. degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool. The base portions of the final blades are axially inserted over the final segments and the latter is displaced radially outwardly and pinned to abut the forward end faces of the final blade base portions.

US Patent:

52115330, May 18, 1993

Filed:

Oct 30, 1991

Appl. No.:

7/785377

Inventors:

Roger C. Walker - Middletown OH
Christopher C. Glynn - Hamilton OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F04D 2958

US Classification:

415115

Abstract:

A method and system for diverting leakage air back into the flow path of a turbine engine. A stator vane assembly is connected to a shroud assembly at the radially inner end of the stator vane assembly, the shroud assembly is provided with a scoop which is placed in the path of leakage air traversing in a forward direction from the high pressure static side of the stator vane to the low static pressure side of the stator vane. The leakage path is located between the stator vane assembly and a rotating member. The scoop intercepts the leakage air and re-directs the leakage air into an airflow path of the turbine engine with an aftward component of velocity.

US Patent:

58532854, Dec 29, 1998

Filed:

Jun 11, 1997

Appl. No.:

8/872840

Inventors:

Frederick Martin Miller - Cincinnati OH
Roger Clayton Walker - Middletown OH
Christopher Charles Glynn - Hamilton OH
Martin C. Hemsworth - Cincinnati OH

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F01D 508
F01D 510

US Classification:

416 96R

Abstract:

In a compressor rotor assembly including a plurality of rotor disks affixed to a rotor body, and wherein at least one radially directed cooling tube is supported from a radially outer end within a rotor shaft, with an opposite, radially inner free end extending toward a longitudinal axis of the rotor, an improvement comprising a ring member loosely secured to the tube at the free end.

US Patent:

53204840, Jun 14, 1994

Filed:

Apr 29, 1993

Appl. No.:

8/055068

Inventors:

Jean-Louis Charbonnel - Le Mee sur Seine, FR
Pierre Debeneix - St Sauveur/Ecole, FR
Christopher C. Glynn - Hamilton OH
Daniel J. Marey - Soisy s/Seine, FR
Jean-Pierre A. J. Mourlan - Boissettes, FR
Jacky S. Naudet - Bondoufle, FR
Gerard Receveur - Nandy, FR
Yann J. M. Rigaud - Pomponne, FR
Roger C. Walker - Middletown OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 900

US Classification:

415115

Abstract:

A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.

US Patent:

52114074, May 18, 1993

Filed:

Apr 30, 1992

Appl. No.:

7/876602

Inventors:

Christopher C. Glynn - Hamilton OH
Roger C. Walker - Middletown OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F16J 1532
F01B 532

US Classification:

277192

Abstract:

A seal assembly for use in a compressor stage of a turbine engine having a rotor disk which is attached to a plurality of rotor blades. Each rotor blade has an axially oriented dovetail attachment which connects to the rotor disk. Each rotor blade has an aftward side which is in contact with a high pressure region and a forward side which is in contact with a low pressure region. A plurality of seal segments form an annular ring located radially inward from the plurality of rotor blades. Each seal segment has an offset center of gravity which causes each seal segment to be securely attached to the rotor disk as centrifugal forces act upon each seal segment during rotation.

US Patent:

53514785, Oct 4, 1994

Filed:

May 29, 1992

Appl. No.:

7/891494

Inventors:

Roger C. Walker - Middletown OH
Richard J. Fallon - West Chester OH
Harold P. Rieck - West Chester OH
John D. Bibler - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 618

US Classification:

60 3907

Abstract:

An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casing and spaced radially inwardly therefrom to define a plenum, two radial discs extending inwardly from the outer casing defining a plenum, a plurality of small area bleed openings located in the inner casing for imparting a radial velocity to the bleed air greater than the circumferential velocity entering the plenum, an air tube located over each bleed opening, and a baffle plate located on top of the air tubes and communicating with the radial discs for supporting the casings, whereby the bleed air impinges on the outer casing and controls distortion by sufficiently reducing the circumferential temperature gradient forming at the outer casing.

US Patent:

51829061, Feb 2, 1993

Filed:

Apr 3, 1992

Appl. No.:

7/864189

Inventors:

Alan R. Gilchrist - Fairfield OH
Thomas J. Sullivan - Fairfield OH
Roger C. Walker - Middletown OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02K 300

US Classification:

602261

Abstract:

A gas turbine engine has a forward rotor, a row of fan blades radially extending from the rotor, and a core turbine engine located rearwardly of the fan blades and rotor and coupled to the rotor for rotatably driving the rotor. An outer annular nacelle surrounds the rotor, fan blades and core engine. An inner annular splitter fairing is disposed rearwardly of the fan blades, surrounds the core engine, and is spaced radially inwardly from the nacelle so as to define therebetween a bypass air flow duct located outwardly from the core engine and rearwardly of the fan blades for producing thrust upon rotation of the rotor and fan blades. A hybrid shape spinner nose is attached about the rotor and projects forwardly therefrom within the nacelle and forwardly of the fan blades. The hybrid shape spinner nose has a forward substantially conical section spaced forwardly of the fan blades, a rearward substantially conical section projecting forwardly of and merging rearwardly with the fan blades, and a transition connecting the forward and rearward sections such that the spinner nose is provided with a compound, substantially conical configuration in which the slope of the forward substantially conical section is greater than the slope of an imaginary conical surface connecting a front end of the spinner nose and a leading edge of the annular splitter fairing, whereas the slope of the rearward substantially conical section is less than the slope of such imaginary conical surface.