Patents by Inventor Ralph J. Thompson
Ralph J. Thompson 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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Patent number: 8052385Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.Type: GrantFiled: March 15, 2010Date of Patent: November 8, 2011Assignee: United Technologies CorporationInventors: Ralph J. Thompson, Susan M. Tholen
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Patent number: 7941920Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.Type: GrantFiled: March 15, 2010Date of Patent: May 17, 2011Assignee: United Technologies CorporationInventors: Ralph J. Thompson, Susan M. Tholen
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Publication number: 20110016689Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.Type: ApplicationFiled: March 15, 2010Publication date: January 27, 2011Applicant: United Technologies CorporationInventors: Ralph J. Thompson, Susan M. Tholen
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Publication number: 20100223790Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.Type: ApplicationFiled: March 15, 2010Publication date: September 9, 2010Applicant: United Technologies CorporationInventors: Ralph J. Thompson, Susan M. Tholen
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Patent number: 7721433Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.Type: GrantFiled: March 28, 2005Date of Patent: May 25, 2010Assignee: United Technologies CorporationInventors: Ralph J. Thompson, Susan M. Tholen
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Publication number: 20090110546Abstract: Feather seals and gas turbine engine systems involving such seals are provided. In this regard, a representative feather seal for a gas turbine engine includes: an elongate body portion; and a locating tab extending longitudinally along the body portion and extending outwardly therefrom.Type: ApplicationFiled: October 29, 2007Publication date: April 30, 2009Applicant: UNITED TECHNOLOGIES CORP.Inventors: Susan M. Tholen, Ralph J. Thompson
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Patent number: 5538393Abstract: A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel having a bend passage which includes a purge hole to avoid separating flow in the bend passage.Type: GrantFiled: January 31, 1995Date of Patent: July 23, 1996Assignee: United Technologies CorporationInventors: Ralph J. Thompson, Daniel E. Kane, Robert W. Sunshine
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Patent number: 5486090Abstract: A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel and a trailing edge serpentine channel. Both serpentine channels include ducts that extend to the serpentine channels from a point inward of adjacent retaining hooks. Cooling fluid flowing onto the outward surface of the segments flows through the ducts and along the serpentine channels to cool the leading and trailing edges of the segments.Type: GrantFiled: March 30, 1994Date of Patent: January 23, 1996Assignee: United Technologies CorporationInventors: Ralph J. Thompson, Daniel E. Kane
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Patent number: 5423659Abstract: A shroud segment for a gas turbine engine includes a hook having an undercut surface. Various construction details are developed that provide a segment having a hook with minimized bending stress. In a particular embodiment, a shroud segment includes a plurality of hooks spaced along the leading and trailing edges of the shroud segment. Each of the plurality of hooks includes a positioning surface, a support surface and an undercut surface therebetween. The positioning surface defines the limits of axial movement of the shroud segment. The support surface reacts the radial loading on the shroud segment during operation of the gas turbine engine. The undercut surface is offset from the stator assembly to define the maximum length of the support surface.Type: GrantFiled: April 28, 1994Date of Patent: June 13, 1995Assignee: United Technologies CorporationInventor: Ralph J. Thompson
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Patent number: 4476535Abstract: A system is provided for gathering information concerning power consumption at different locations, generating signals corresponding to this power consumption, transmitting the signals to a selected location and conditioning the signals for recording and subsequent analysis by computer. The signals have frequencies proportional to the power consumption monitored plus a preselected offset frequency which can be synchronized with an outside source such as the line frequency of readily available power lines.Type: GrantFiled: June 15, 1981Date of Patent: October 9, 1984Inventors: Clement T. Loshing, Ralph J. Thompson
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Patent number: 4300125Abstract: A system is provided for gathering information concerning power consumption at different locations, generating signals corresponding to this power consumption, transmitting the signals to a selected location and conditioning the signals for recording and subsequent analysis by computer. The signals have frequencies proportional to the power consumption monitored plus a preselected offset frequency which can be synchronized with an outside source such as the line frequency of readily available power lines.Type: GrantFiled: June 1, 1979Date of Patent: November 10, 1981Inventors: Clement T. Loshing, Ralph J. Thompson