Sami M Aslam

US Patent:

6334310, Jan 1, 2002

Filed:

Jun 2, 2000

Appl. No.:

09/586043

Inventors:

Maz Sutcu - Niskayuna NY
Bernard Arthur Couture - Latham NY
Sami Aslam - Clifton Park NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 100

US Classification:

60752, 29888061, 228164

Abstract:

A combustion liner and cooling sleeve assembly for a turbine combustor includes a substantially cylindrical combustion liner; and a substantially cylindrical outer cooling sleeve surrounding at least an axial portion of the combustion liner; wherein the outer cooling sleeve is secured to the combustion liner by a weld at one end of the cooling sleeve at its aft end, with a predetermined radial gap therebetween, the gap determined by respective operating temperatures and thermal expansion coefficients. A method of reducing crack propensity in a substantially cylindrical combustion liner and substantially cylindrical cooling sleeve assembly where one end of said cooling sleeve is welded to the combustion liner, includes the steps of: a) determining a radial gap between the combustion liner and the outer cooling sleeve as a function of operating temperatures and thermal expansion coefficients of the liner and the cooling sleeve; b) forming the outer cooling sleeve with a diameter sufficient to provide the radial gap; c) swaging the outer end of the cooling sleeve to bring the end of the outer cooling sleeve into engagement With the combustion liner; and d) welding the outer cooling sleeve to the combustion liner.

US Patent:

6532840, Mar 18, 2003

Filed:

Dec 19, 2000

Appl. No.:

09/739355

Inventors:

Kenneth John Hatley - Madison NJ
Richard Michael Hatley - Madison NJ
Sean Michael McDonnell - Aberdeen NJ
Michael John Bousquet - West Milford NJ
Thomas Arthur Wagner - Troy NY
Sami Aslam - Clifton Park NY
Kathleen Lynne Bentzel - Scotia NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

G01D 526

US Classification:

738665, 3562411

Abstract:

The method for in situ inspection includes providing a pair of adjacent impingement sleeves forming part of a combustor. A robotic inspection tool carrying an inspection head is inserted through an opening in the outer casing of the gas turbine and manipulated to locate the inspection head between the adjacent impingement sleeves. After inspecting the exterior surface of an impingement sleeve, the inspection tool is withdrawn from the casing. Additionally, a transition piece body forming part of a combustor is inspected by securing a robotic manipulator to an open end of the combustion casing, locating an inspection head on an inspection arm of the manipulator and manipulating the arm to locate the inspection head to inspect interior wall portions of the transition body by displacing the head axially and radially toward wall portions of the transition body. Side seam welds of the transition piece body are also inspected by providing a guide with a contoured surface corresponding to the contour of the side seam weld and displacing an inspection head along the guide through the transition piece body and impingement sleeve to inspect the weld of the transition piece body.

US Patent:

6704688, Mar 9, 2004

Filed:

Oct 16, 2001

Appl. No.:

09/977365

Inventors:

Sami Aslam - Clifton Park NY
Donald Ernest Woodmansee - Simponsville SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

G01B 700

US Classification:

702182, 702176, 702187, 708139, 708142

Abstract:

A method of inspecting and recording inspection data of machine components, the method including selecting a machine component among a plurality of machine components for inspection; identifying predefined areas of the selected machine component for inspection; identifying a fixed set of conditions allowed to be reported for the select machine component; inspecting the predefined areas of the select machine component; and recording inspection data as continuous numerical values to quantify entry for subsequent querying over a chosen set of machine components.

US Patent:

20020121744, Sep 5, 2002

Filed:

Mar 5, 2001

Appl. No.:

09/798842

Inventors:

Mahmut Aksit - Troy NY, US
Jeffrey Benoit - Scotia NY, US
Sami Aslam - Clifton Park NY, US
Robert Bland - Oviedo FL, US
Bharat Bagepalli - Niskayuna NY, US

Assignee:

General Electric Company

International Classification:

F16J015/44

US Classification:

277/411000

Abstract:

Metallic cloth seals backed by stiff high temperature-resistant shims depend from a bracket for engagement in a slot of a transition piece for sealing between the transition piece and a first-stage nozzle. The high pressure acting on the shim forces the metallic cloth into engagement with the sealing surface in the slot. The lower edge of the shim is bent about, and overlies, the edge of the metallic cloth in a direction toward the sealing surface of the slot to choke any flow from the high pressure region past the seal. Elongated spline seals are also inserted into opposed registering slots of adjacent transition pieces. The spline seals comprise metallic cloth folded onto itself backed by elongated stiff high temperature-resistant shims having lateral edges overlying the lateral edges of the cloth material. The overlying edges prevent leakage flow about the spline seals from the high pressure to the low pressure regions.

US Patent:

61620149, Dec 19, 2000

Filed:

Sep 22, 1998

Appl. No.:

9/158738

Inventors:

Bharat Sampathkumar Bagepalli - Niskayuna NY
Sami Aslam - Clifton Park NY
Leslie Boyd Bedell - Niskayuna NY
Mahmut Faruk Aksit - Troy NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 500

US Classification:

4151701

Abstract:

A turbine spline seal includes an elongated turbine seal member. The seal member has an elongated, imperforate, and manually-flexible first portion and a manually-rigid second portion lengthwise adjoining the first portion. The turbine assembly includes the turbine spline seal and also includes first and second turbine members. The first and second turbine members are spaced apart to define a fluid-path leakage gap therebetween, and the seal member is placed in the gap. Each lengthwise edge of the seal member engages a respective one of two opposing surface grooves of the first and second turbine members.