MOHAMMAD E TASLIM
Broker in Needham, MA

6607356, Aug 19, 2003

Jan 11, 2002

10/044249

Robert Francis Manning - Newburyport MA
Mohammad Esmail Taslim - Needham MA

General Electric Company - Schenectady NY

F01D 518

416 97R

A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row of inlet holes, and a row of outlet holes extends from the second channel toward the trailing edge of the airfoil. A row of turbulator ribs is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.

5013340, May 7, 1991

Jun 29, 1989

7/374078

Mohammad E. Taslim - Needham MA
Yiannis A. Levendis - Boston MA

Northeastern University - Boston MA

B01D 4638

55290

A rotating particulate trap is disclosed, which may find application in diesel engines, air conditioning systems, industrial air-filters and the like. The invention includes a disk or cylinder which is formed from material suitable for filtering particulates which are present in the exhaust gases of diesel engines, gas turbines, industrial air or other particulate laden gases. The disk is mounted transversely in the exhaust duct of a diesel engine and in a fresh air duct which is disposed parallel to the exhaust duct. As the disk rotates within the exhaust duct, it filters particulates from the exhaust gases of the diesel engine. The filtered particulates are expelled from the disk by fresh air blowing in the air duct as the disk rotates within the air duct. The fresh air is blown in the air duct in a direction opposite to the flow of exhaust gases within the exhaust duct by a fan or compressor or compressed air jets. The counterflow arrangement of fresh air and combustion gases enhances the effectiveness of particulate removal as the disk rotates between the exhaust duct and the fresh air duct.

5472316, Dec 5, 1995

Sep 19, 1994

8/308227

Mohammad E. Taslim - Needham MA
Samuel D. Spring - Stratham NH
Thomas E. Demarche - Boxford MA

General Electric Company - Cincinnati OH

F01D 518

416 97R

An improved cooling passage configuration for a gas turbine engine airfoil is disclosed for enhancing convective cooling over that afforded by conventional wall turbulator ribs. An internal cooling passage bounded by pressure and suction side walls and at least one partition has raised turbulator ribs disposed on at least one side wall and the partition. A side wall turbulator rib extends over at least a portion of the side wall and abuts the partition. A turbulator rib disposed on the partition extends from a point spaced from the wall rib to the opposed side wall. The gap formed between the partition rib and wall rib accelerates a coolant flow passing therethrough, locally enhancing convective heat transfer. Partition ribs may be aligned with or offset from the wall ribs in the spanwise direction and may be normal to the primary direction of cooling flow or angled thereto. Convective heat transfer is particularly enhanced in flow passages having cavity height blockage due to wall ribs greater than about 10%.

6890153, May 10, 2005

Apr 29, 2003

10/425262

Daniel Edward Demers - Ipswich MA, US
Mohammad Esmaail Taslim - Needham MA, US

General Electric Company - Schenectady NY

F01D005/08

416 97R, 416 96 R, 415 1, 415115

A turbine airfoil includes pressure and suction sidewalls joined together at opposite leading and trailing edges, and at a forward bridge spaced behind the leading edge to define a flow channel. The bridge includes a row of impingement holes. The flow channel includes a row of fins behind the leading edge, a row of first turbulators behind the pressure sidewall, and row of second turbulators behind the suction sidewall. The fins and turbulators have different configurations for increasing internal surface area and heat transfer for back side cooling the leading edge by the cooling air.

6132169, Oct 17, 2000

Dec 18, 1998

9/215858

Robert F. Manning - Newburyport MA
Robert B. Solda - Peabody MA
Lalit K. Parekh - Marblehead MA
Mohammad E. Taslim - Needham MA

General Electric Company - Cincinnati OH

F01D 514

415115

A turbine engine airfoil includes a three-pass serpentine shaped cooling cavity including a leading edge chamber, an oversized intermediate chamber, and a trailing edge chamber in flow communication. The cavity further includes a combination of a plurality of ribs and a plurality of pins, a purge air swirler, a turning vane, and a metering partition which mixes the high pressure air and provides increased air cooling and uniform flow control in the airfoil. The metering partition provides a decrease of the air pressure in the trailing edge chamber allowing for an increase in the number of trailing edge slots.

5681144, Oct 28, 1997

Dec 17, 1991

7/809193

Samuel Dale Spring - Stratham NH
Nesim Abuaf - Schenectady NY
Mohammad Esmail Taslim - Needham MA

General Electric Company - Cincinnati OH

F01D 518

416 97R

A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.