SYED HASSAN KHALID JAFRI, MD
Osteopathic Medicine at Deyoung St, Marion, IL

6606854, Aug 19, 2003

Apr 18, 2000

09/551728

Robert G. Siefker - Greenwood IN
Baily Ramachandra Vittal - Carmel IN
Von David Baker - Indianapolis IN
Syed Arif Khalid - Indianapolis IN
James Carl Loebig - Indianapolis IN

Allison Advanced Development Company - Indianapolis IN

F02K 148

60262, 60264, 2391273, 23926519, 181213, 181220

Disclosed is an exhaust mixer ( ) including a passage ( ) extending from an inlet ( ) to an outlet ( ) that is coincident with a centerline axis of mixer ( ). Several ridges ( ) are circumferentially disposed about the axis and each flare away from the centerline axis relative to a direction along the centerline axis from inlet ( ) toward outlet ( ). Ridges ( ) each define a corresponding one of several inner channels ( ) radially disposed about passage ( ) that each intersect passage ( ) between inlet ( ) and outlet ( ). Several outer channels ( ) are also radially disposed about passage( ) and are each positioned between a corresponding pair of inner channels ( ). Ridges are each shaped to turn inner channels ( and outer channels ( ) about the axis as ridges ( ) extend along the indicated direction. Inner channels ( ) diverge away from the axis and one another in this direction while outer channels ( ) converge toward the axis and one another in this direction.

6568909, May 27, 2003

Sep 26, 2001

09/964019

Peter Nicholas Szucs - West Chester OH
Gregory Scott McNulty - Shelbyville IN
Syed Arif Khalid - Indianapolis IN
David William Crall - Loveland OH

General Electric Company - Schenectady NY

F01D 520

416228, 298897

An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.

2008004, Feb 21, 2008

Aug 15, 2006

11/505129

Syed Arif Khalid - Indianapolis IN, US

F01D 1/02

415 574

A turbomachine is provided having at least one row of blades oriented at a predetermined stagger. Casing grooves are provided proximate to at least a portion of the tip of the blades. The grooves are oriented substantially normal to the stagger of the blades. The normal of the blade is determined from a chord of the blade. The chord may be taken across a pair of corresponding points one the upstream and downstream end of the blade, hence across the extent of the cross-sectional shape of the blade. Alternatively, a blade chord may be determined over only a portion of the blade, for instance, from a point along the centerline of the upstream end of the blade to a second point on the centerline midway down the blade from the upstream end. Optimally, the grooves are positioned adjacent to the upstream half of the blades, but may continue across the axial extent of the blades. The spacing between grooves can be optimized for blade stagger in order to find an optimal number of grooves that concurrently cross the blade. Additionally, obtaining an optimal groove depth for a particular turbomachine requires knowing only the tip clearance gap as groove depth is directly related to the tip clearance. Furthermore, since the groove may be substantially smaller than prior art casing treatments, fluid recirculation is reduced. The blade-normal groove may take a variety of cross-sectional shapes. Optimally, the aft surface of the groove will have less than a 45° incline to the radial at that point.

2004006, Apr 15, 2004

Jun 10, 2003

10/457938

Robert Siefker - Greenwood IN, US
Baily Vittal - Carmel IN, US
Von Baker - Indianapolis IN, US
Syed Khalid - Indianapolis IN, US
James Loebig - Indianapolis IN, US

F02K001/38

060/262000

Disclosed is an exhaust mixer () including a passage () extending from an inlet () to an outlet () that is coincident with a centerline axis of mixer (). Several ridges () are circumferentially disposed about the axis and each flare away from the centerline axis relative to a direction along the centerline axis from inlet () toward outlet (). Ridges () each define a corresponding one of several inner channels () radially disposed about passage () that each intersect passage () between inlet () and outlet (). Several outer channels () are also radially disposed about passage () and are each positioned between a corresponding pair of inner channels (). Ridges are each shaped to turn inner channels (and outer channels () about the axis as ridges () extend along the indicated direction. Inner channels () diverge away from the axis and one another in this direction while outer channels () converge toward the axis and one another in this direction.

2011027, Nov 17, 2011

Jul 26, 2011

13/191038

Syed Jalaluddin Khalid - Indianapolis IN, US

F02C 7/00, B64D 33/02

60772, 60 395, 244 53 B

The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. A moveable shroud can be used to open and close a passage of an ejector which can be used to assist in withdrawing a boundary layer or entrain an ambient air. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.

2010016, Jul 1, 2010

Oct 23, 2009

12/604776

Syed Jalaluddin Khalid - Indianapolis IN, US

F02K 3/04

60204, 602261

The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.

8572947, Nov 5, 2013

Oct 23, 2009

12/604759

Syed Jalaluddin Khalid - Indianapolis IN, US

Rolls-Royce Corporation - Indianapolis IN

F02K 3/02

602261, 60262

The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.

7320575, Jan 22, 2008

Sep 28, 2004

10/952184

Aspi Rustom Wadia - Loveland OH, US
Peter Nicholas Szucs - West Chester OH, US
Syed Arif Khalid - Indianapolis IN, US
Peter John Wood - Loveland OH, US
Kevin R. Kirtley - Scotia NY, US
Xiaoyue Liu - Clifton NY, US

General Electric Company - Schenectady NY

B63H 1/14

416 97R, 415115, 415116

An airfoil having a root, a tip, and an outer surface for pressuring air flowable thereover. The outer surface includes one or more slots elongate in a direction selected to preclude or reduce circulation within the slots, and the one or more slots are configured to bleed a boundary layer from the outer surface to the tip utilizing one or more passageways within the airfoil.