Wieslaw A Chlus

6802691, Oct 12, 2004

Nov 19, 2002

10/299634

Wieslaw Chlus - Wethersfield CT

United Technologies Corporation - Hartford CT

F01D 1712

415145, 415221

The present invention relates to an axial flow rotary machine and to a maintainable compressor bleed system therefore. The axial flow rotary machine comprises a primary flow path for a working medium, a secondary flow path for the working medium, a bleed system for allowing a bleed portion of the working medium flowing in the primary flow path to be delivered to the secondary flow path, a support structure for the bleed system located radially inboard of the bleed system, and the panels for gaining access to the bleed system. The panels are located radially outboard of the bleed system. The panels form the inner flow wall for the primary flow path.

6824359, Nov 30, 2004

Jan 31, 2003

10/355664

Wieslaw A. Chlus - Wethersfield CT
Stanley J. Funk - New Britain CT

United Technologies Corporation - Hartford CT

F01D 518

416 92, 416 97 R

A turbine blade has a platform and an airfoil extending from a root at the platform to a tip. The airfoil has an internal cooling passageway network including at least one trailing edge cavity. A group of trailing edge holes extends from the trailing edge to the trailing edge cavity and a group of tip holes extends from the tip to the trailing edge cavity.

6951447, Oct 4, 2005

Dec 17, 2003

10/738288

Anthony Cherolis - East Hartford CT, US
Wieslaw A. Chlus - Wethersfield CT, US

United Technologies Corporation - Hartford CT

F01D005/14

416193A

A turbine blade has an undercut beneath its platform at a trailing edge. The undercut has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets at upper and lower extents of the undercut with an intermediate straight section. The intermediate straight section is preferably parallel to a principle stress field of the platform.

7059834, Jun 13, 2006

Jan 24, 2003

10/350635

Wieslaw A. Chlus - Wethersfield CT, US
Stanley J. Funk - New Britain CT, US

United Technologies Corporation - Hartford CT

F01D 5/18

416 92, 416 97 R

A turbine blade tip plenum has means for preferentially directing or diverting cooling air from a cooling passageway network to cool areas subject to extreme heat.

7175386, Feb 13, 2007

Dec 17, 2003

10/738842

Anthony Cherolis - East Hartford CT, US
Wieslaw A. Chlus - Wethersfield CT, US

United Technologies Corporation - Hartford CT

F01D 5/14

415115, 416 97 R

A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.

7175391, Feb 13, 2007

Jul 8, 2004

10/888125

Wieslaw A. Chlus - Wethersfield CT, US
Jesse R. Christophel - Vernon CT, US

United Technologies Corporation - Hartford CT

B64C 11/24

416 92, 416 96 A, 416 96 R

A blade has an airfoil body having an internal cooling passageway network and a body tip pocket. At least one plate is secured within the body tip pocket and has inboard and outboard surfaces. A recess is in the outboard surface and an associated protrusion is on the inboard surface.

7575416, Aug 18, 2009

May 18, 2006

11/437189

Stanley J. Funk - New Britain CT, US
Wieslaw A. Chlus - Wethersfield CT, US

United Technologies Corporation - Hartford CT

F01D 5/30

416193A, 416219 R, 416239

A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high temperature material is disposed between the root sections of adjacent rotor blades and engages the blades under operative conditions.

7726944, Jun 1, 2010

Sep 20, 2006

11/524102

Richard H. Page - Guilford CT, US
Wieslaw A. Chlus - Wethersfield CT, US

United Technologies Corporation - Hartford CT

F01D 5/18

416 92

A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.