Kenneth E Hall

US Patent:

58167773, Oct 6, 1998

Filed:

Nov 29, 1991

Appl. No.:

7/799650

Inventors:

Kenneth B. Hall - Jupiter FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

Internal heat transfer of air cooled turbine blades of a gas turbine engine is enhanced by orienting the impingement holes that interconnect the air-cooled feed passage to the hybrid passageway internally of the blade in a more radial direction to minimize pressure drop losses. By improved mixing of the cooling air in the hybrid passageway the additional mechanical turbulence promoters can be utilized without sacrificing pressure losses.

US Patent:

48201227, Apr 11, 1989

Filed:

Apr 25, 1988

Appl. No.:

7/185227

Inventors:

Kenneth B. Hall - Jupiter FL
Thomas A. Auxier - Palm Beach Gardens FL
Wesley D. Brown - Jupiter FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

Dirt removal means for an internally air cooled blade for a gas turbine engine of the type that includes multi passes some of which are serpentine as made in situ by casting the ribs so as to be angularly disposed at the root of the blade and a straight through passageway with an opening at the tip. The velocity of the airstream in the straight through passageway being sufficiently high to carry the dirt through the opening and the angularly disposed ribs overlying the entrance to the other passageway so as to divert the dirt entrained airstream into the straight through passageway while allowing relatively dirt-free air to turn the angle of the rib to enter the serpentine passes.

US Patent:

48591475, Aug 22, 1989

Filed:

Jan 25, 1988

Appl. No.:

7/147465

Inventors:

Kenneth B. Hall - Jupiter FL
Kenneth K. Landis - Tequesta FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

The airfoil shaped body has a separate leading edge portion (14) spaced from the main body (12). Slots (22) thereby formed discharge cooling air parallel to surface (38) of the main body. A step change across the slot between the leading edge surface (52) and the main body surface (38) facilitates smooth introduction of cooling air.

US Patent:

48275875, May 9, 1989

Filed:

Jan 25, 1988

Appl. No.:

7/147464

Inventors:

Kenneth B. Hall - Jupiter FL
Kenneth K. Landis - Tequesta FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B21K 304

US Classification:

291568B

Abstract:

A turbine blade is formed from an airfoil blade 10 having V-grooves 12 in the outer surface and indentations 26 in the inner surface. A slot 30 is machined at the root of the groove intersecting the slots, and providing a smooth flow path for the cooling air discharging along the blade surface.

US Patent:

52437590, Sep 14, 1993

Filed:

Oct 7, 1991

Appl. No.:

7/772296

Inventors:

Wesley D. Brown - Jupiter FL
Kenneth B. Hall - Jupiter FL
Robert J. Kildea - North Palm Beach FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 910
B23P 1502

US Classification:

29889721

Abstract:

The flow rate of the cooling air at the trailing edge of the airfoil of a turbine blade for a gas turbine engine is established by casting the blade to include judiciously located radially spaced projections adjacent to or in the ribs in the trailing edge which serve to meter the flow in the channels formed between the ribs. The holes for forming the projections in the core that are used to form the internal cooling passages in the trailing edge are intentionally undersized. After the core is cleaned and flashed, the blade is cast in a mold and the ceramic core is leached out. The internal cooling passages in the trailing edge are flow tested to obtain the flow rate and pressure and this data is used to resize the projection. Resizing the projection is made by reforming the core with the same die, and with the information previously obtained in the flow test, the holes that form the projections are enlarged by drilling to obtain the desired flow rate. This process is repeated until the desired flow rate for each trailing edge channel is achieved.

US Patent:

54860938, Jan 23, 1996

Filed:

Sep 8, 1993

Appl. No.:

8/118158

Inventors:

Thomas A. Auxier - Palm Beach Gardens FL
Kenneth B. Hall - Jupiter FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B63H 114

US Classification:

416 97R

Abstract:

The leading edge of the turbine airfoil of a turbine blade for a gas turbine engine is cooled by utilizing helix shaped holes that are rectangular in cross-section and curved to produce film holes egressing at low angles adjacent the outer surface of the leading edge. The helix holes extend from the root to the tip of the blade and are parallelly and longitudinally spaced.

US Patent:

56740506, Oct 7, 1997

Filed:

Dec 5, 1988

Appl. No.:

7/279632

Inventors:

Kenneth B. Hall - Jupiter FL
Thomas A. Auxier - Palm Beach Gardens FL

Assignee:

United Technologies Corp. - Hartford CT

International Classification:

E01D 518

US Classification:

416 97R

Abstract:

A bulkhead in the form of a rib extending spanwise adjacent the leading edge of the airfoil of a turbine blade of a gas turbine engine serves to stiffen the airfoil to attain protection from impact by foreign objects, but doesn't materially affect cooling effectiveness in the event of a puncture of the skin. Holes extending spanwise in the rib reduce the mass, allow radial flow, and restrict flow into the leading edge. This construct allows a reduction in the thickness of the skin of the airfoil, and hence a weight reduction.

US Patent:

57001316, Dec 23, 1997

Filed:

Aug 24, 1988

Appl. No.:

7/236093

Inventors:

Kenneth B. Hall - Jupiter FL
Robert J. McClelland - Palm Beach Gardens FL
Thomas A. Auxier - Palm Beach Gardens FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

An internally cooled turbine blade for a gas turbine engine is modified at the leading and trailing edges to include a dynamic cool air flowing radial passageway with an inlet at the root and a discharge at the tip feeding a plurality of radially spaced film cooling holes in the airfoil surface. Replenishment holes communicating with the serpentine passages radially spaced in the inner wall of the radial passage replenish the cooling air lost to the film cooling holes. The discharge orifice is sized to match the backflow margin to achieve a constant film hole coverage throughout the radial length. Trip strips may be employed to augment the pressure drop distribution.