Patents by Inventor Panagiota Tsifourdaris
Panagiota Tsifourdaris 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: 20190063242Abstract: A power turbine includes a second stage vane having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: August 31, 2017Publication date: February 28, 2019Inventor: Panagiota TSIFOURDARIS
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Patent number: 9909434Abstract: An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of circumferentially spaced-apart vanes extending radially across the flow passage. At least one of the struts is aligned in the circumferential direction with an associated one of the vanes and forms therewith an integrated strut-vane airfoil. The adjacent vanes on opposed sides of the integrated strut-vane airfoil have uneven axial chords relative to the other vanes.Type: GrantFiled: November 12, 2015Date of Patent: March 6, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Panagiota Tsifourdaris, Edward Vlasic, Niloofar Moradi, Francois Doyon
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Publication number: 20170022832Abstract: An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of circumferentially spaced-apart vanes extending radially across the flow passage. At least one of the struts is aligned in the circumferential direction with an associated one of the vanes and forms therewith an integrated strut-vane airfoil. The adjacent vanes on opposed sides of the integrated strut-vane airfoil have uneven axial chords relative to the other vanes.Type: ApplicationFiled: November 12, 2015Publication date: January 26, 2017Inventors: PANAGIOTA TSIFOURDARIS, EDWARD VLASIC, NILOOFAR MORADI, FRANCOIS DOYON
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Patent number: 8979487Abstract: A high pressure turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: April 11, 2012Date of Patent: March 17, 2015Assignee: Pratt & Whitney Canada Corp.Inventors: Panagiota Tsifourdaris, Raja Ramamurthy
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Publication number: 20140255159Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.Type: ApplicationFiled: March 7, 2013Publication date: September 11, 2014Applicant: Pratt & Whitney Canada Corp.Inventors: VINCENT PARADIS, EDWARD VLASIC, PANAGIOTA TSIFOURDARIS
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Publication number: 20130272887Abstract: A high pressure turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: April 11, 2012Publication date: October 17, 2013Inventors: Panagiota Tsifourdaris, Raja Ramamurthy
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Patent number: 8439645Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: March 30, 2010Date of Patent: May 14, 2013Assignee: Pratt & Whitney Canada Corp.Inventor: Panagiota Tsifourdaris
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Patent number: 8182204Abstract: A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.Type: GrantFiled: April 24, 2009Date of Patent: May 22, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, Mohamad Sleiman, Panagiota Tsifourdaris
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Patent number: 8167568Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: March 26, 2010Date of Patent: May 1, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Panagiota Tsifourdaris
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Patent number: 8105043Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: April 1, 2010Date of Patent: January 31, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Panagiota Tsifourdaris
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Publication number: 20110243748Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: March 30, 2010Publication date: October 6, 2011Inventor: Panagiota Tsifourdaris
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Publication number: 20110236214Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: March 26, 2010Publication date: September 29, 2011Inventor: Panagiota TSIFOURDARIS
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Publication number: 20100329874Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: April 1, 2010Publication date: December 30, 2010Inventor: Panagiota Tsifourdaris
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Publication number: 20100272566Abstract: A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.Type: ApplicationFiled: April 24, 2009Publication date: October 28, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Eric DUROCHER, Mohamad SLEIMAN, Panagiota TSIFOURDARIS
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Patent number: 7625183Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: September 5, 2006Date of Patent: December 1, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Panagiota Tsifourdaris, Sami Girgis
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Patent number: 7559746Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: July 14, 2009Assignee: pratt & Whitney Canada Corp.Inventors: Panagiota Tsifourdaris, Krishan Mohan, Sami Girgis
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Publication number: 20080118358Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: November 22, 2006Publication date: May 22, 2008Inventors: Panagiota Tsifourdaris, Krishan Mohan, Sami Girgis
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Patent number: 7367779Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: March 2, 2006Date of Patent: May 6, 2008Assignee: Pratt & Whitney Canada Corp.Inventors: Sami Girgis, Panagiota Tsifourdaris
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Publication number: 20080056894Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: September 5, 2006Publication date: March 6, 2008Inventors: Panagiota Tsifourdaris, Sami Girgis
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Publication number: 20070207037Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: March 2, 2006Publication date: September 6, 2007Inventors: Sami Girgis, Panagiota Tsifourdaris