Patents by Inventor William Patrick Allen
William Patrick Allen has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20020130047Abstract: According to the invention, an article that is exposed to high temperature e.g., over 1000° C. during operation is disclosed. In one embodiment, a method for a gas turbine engine includes a directionally solidifed metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY or a noble metal containing aluminide or corrosion inhibiting ceramic is located on portions or the blade not previously covered with such coatings, e.g., the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also created, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.Type: ApplicationFiled: January 29, 2002Publication date: September 19, 2002Applicant: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson, Dilip M. Shah, Alan David Cetel
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Publication number: 20020119043Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000 ° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.Type: ApplicationFiled: April 16, 2001Publication date: August 29, 2002Inventors: William Patrick Allen, Walter E. Olson
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Patent number: 6435835Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.Type: GrantFiled: December 20, 1999Date of Patent: August 20, 2002Assignee: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson
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Patent number: 6435826Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.Type: GrantFiled: April 16, 2001Date of Patent: August 20, 2002Assignee: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson
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Patent number: 6435830Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.Type: GrantFiled: December 20, 1999Date of Patent: August 20, 2002Assignee: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson, Dilip M. Shah, Alan David Cetel
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Patent number: 6410148Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a barium-strontium alumino silicate.Type: GrantFiled: April 15, 1999Date of Patent: June 25, 2002Assignees: General Electric Co., United Technologies Corp., The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Nathan S. Jacobson, Nanottam P. Bansal, Elizabeth J. Opila, James L. Smialek, Kang N. Lee, Irene T. Spitsberg, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6387456Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a barium-strontium alumino silicate.Type: GrantFiled: September 5, 2000Date of Patent: May 14, 2002Assignees: General Electric Company, United Technologies Corporation, The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Nathan S. Jacobson, Narottam P. Bansal, Elizabeth J. Opila, James L. Smialek, Kang N. Lee, Irene T. Spitsberg, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6312763Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a yttrium silicate.Type: GrantFiled: November 16, 2000Date of Patent: November 6, 2001Assignees: United Technologies Corporation, General Electric Co., NASAInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Nathan S. Jacobson, Kang N. Lee, Elizabeth J. Opila, James L. Smialek, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6296941Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a yttrium silicate.Type: GrantFiled: April 15, 1999Date of Patent: October 2, 2001Assignees: General Electric Company, United Technologies Corporation, NASAInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Nathan S. Jacobson, Kang N. Lee, Elizabeth J. Opila, James L. Smialek, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6296942Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a calcium alumino silicate.Type: GrantFiled: April 15, 1999Date of Patent: October 2, 2001Assignees: General Electric Company, United Technologies Corporation, NASAInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Robert Alden Miller, Nathan S. Jacobson, James L. Smialek, Elizabeth J. Opila, Kang N. Lee, Bangalore A. Nagaraj, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6284325Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a calcium alumino silicate.Type: GrantFiled: November 16, 2000Date of Patent: September 4, 2001Assignees: General Electric Company, United Technologies Corporation, The United States of America as represented by the United States National Aeronautics and Space AdministrationInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Robert Alden Miller, Nathan S. Jacobson, James L. Smialek, Elizabeth J. Opila, Kang N. Lee, Bangalore A. Nagaraj, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Publication number: 20010004474Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a method for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY or a noble metal containing aluminide or corrosion inhibiting ceramic is located on portions or the blade not previously covered with such coatings, e.g., the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.Type: ApplicationFiled: December 13, 2000Publication date: June 21, 2001Applicant: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson, Dilip M. Shah, Alan David Cetel
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Publication number: 20010004475Abstract: According to the invention, an article that is exposed to high temperatures, e.g.. over 1000° C. during operation is disclosed. In one embodiment, a method for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant overlay coating such as an MCrAlY or a noble metal containing aluminide or corrosion inhibiting ceramic is located on portions or the blade not previously covered with such coatings, e.g., the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.Type: ApplicationFiled: December 13, 2000Publication date: June 21, 2001Applicant: United Technologies CorporationInventors: William Patrick Allen, Walter E. Olson, Dilip M. Shah, Alan David Cetel