The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Nov. 23, 2010

Filed:

Mar. 17, 2005
Applicants:

David B. Allen, Oviedo, FL (US);

Ramesh Subramanian, Oviedo, FL (US);

Inventors:

David B. Allen, Oviedo, FL (US);

Ramesh Subramanian, Oviedo, FL (US);

Assignee:

Siemens Energy, Inc., Orlando, FL (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B23P 6/00 (2006.01);
U.S. Cl.
CPC ...
Abstract

A method of forming an interstage seal including removing a diaphragm seal box () from a gas turbine compressor assembly () and removing a labyrinth sealing member () from the diaphragm seal box (). An abradable material layer () may be deposited on the diaphragm seal box (). A spray gun may be mounted in relation to an engine disk () of the gas turbine compressor assembly () for cold-spraying a quantity of particles toward the engine disk (). The particles may be sprayed at a velocity sufficiently high to cause at least a portion of the quantity of particles to adhere to the engine disk (). The spray gun may be controlled to deposit a quantity of particles on the compressor disk () to form a geometry () that will abrade the abradable material layer () during operation of the gas turbine compressor assembly (). The geometry () abrading the abradable material layer () forms an interstage seal. Rotation of the engine disk () within the gas turbine compressor assembly () may be controlled during the step of controlling the spray gun. The diaphragm seal box () may be reinstalled within the gas turbine compressor assembly () so that the geometry () aligns with the abradable material layer ().


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