Patents by Inventor Ian G Martindale
Ian G Martindale 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: 7866939Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade. A set of cassettes (120) carries fan blade track panels (71B, 71C, 71D). The cassettes (120) are secured to the metal casing (40) by axially extending members (124, 128) on the upstream and downstream ends (122, 126) of the cassettes (120) which locate on the annular member (54) and are secured to inserts (136) on the inner face of the casing (40).Type: GrantFiled: October 15, 2004Date of Patent: January 11, 2011Assignee: Rolls-Royce plcInventors: Cedric B Harper, Michael Creagh, Neil Humphries, Ian G Martindale
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Publication number: 20090324390Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). A set of cassettes (120) carries fan blade track panels (71B,71C,71D). The cassettes (120) are secured to the metal casing (40) by axially extending members (124,128) on the upstream and downstream ends (122,126) of the cassettes (120) which locate on the annular member (54) and are secured to inserts (136) on the inner face of the casing (40).Type: ApplicationFiled: October 15, 2004Publication date: December 31, 2009Inventors: Cedric B. Harper, Michael Creagh, Neil Humphries, Ian G. Martindale
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Patent number: 7396203Abstract: A spacer arrangement 1, 40 is provided in which wedges 5, 6; 45, 46 are arranged to have an interface 7, 47 between them such that a thermally variable member 8, 48 can cause relative motion between the wedges 5, 6; 45, 46 to adjust an arrangement lateral dimension dependent upon temperature. In such circumstances with the arrangement 1, 40 positioned within a gap 3 between a casing 14 and unison ring 13, retention of position of that unison ring 13 can be maintained. The unison ring is arranged to adjust position of variable vanes.Type: GrantFiled: June 16, 2005Date of Patent: July 8, 2008Assignee: Rolls-Royce, plcInventor: Ian G. Martindale
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Patent number: 7338250Abstract: A gas turbine engine rotor blade containment assembly (38) comprises a containment casing (40) and the containment casing (40) has a plurality of axially spaced ribs (66). The ribs (66) extend circumferentially and radially inwardly from the containment casing (40) to define a plurality of circumferentially extending grooves (76) and a perforate sheet (70) is secured to the radially inner ends (68) of the ribs (66). In the arrangement of the present invention the blade containment function and the acoustic treatment function are combined.Type: GrantFiled: October 1, 2004Date of Patent: March 4, 2008Assignee: Rolls-Royce plcInventors: Ian G Martindale, Sivasubramaniam K Sathianathan
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Patent number: 6829883Abstract: A joint assembly for limiting an extension of the joint in the direction of a load path derived from an impact comprising a first member having a portion and a second member having a portion, the portions overlapping one another and arranged generally parallel to one another and secured together via securing means disposed through corresponding holes defined therein. One of the overlapping portions further defines, sequentially in the direction of extension, a shear neck, a pocket and a catcher portion. In the event of a worst-case impact load the securing means shears through the shear neck and the pocket and is arrested by the catcher portion, thereby the extension of the joint assembly is limited and the joint assembly remains integral.Type: GrantFiled: July 9, 2002Date of Patent: December 14, 2004Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Peter E Farrington, Ian G Martindale, Caroline McLachlan, Stephen J Booth, Duncan Auterson, David S Yazdani
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Patent number: 6769864Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54) and a downstream portion (60). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54) and the downstream portion (60). The downstream portion (60) has impact protection means (64) located on its inner surface (62) to protect the downstream portion (60) of the containment casing (40). The impact protection means (64) comprises a plurality of radially inwardly and circumferentially extending ribs (80) on the inner surface (62) of the downstream portion (60) to act as spacer between an inner portion of a detached fan blade (34) and the downstream portion (60).Type: GrantFiled: March 18, 2002Date of Patent: August 3, 2004Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Stephen J Booth, Ian G Martindale
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Patent number: 6739830Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.Type: GrantFiled: October 29, 2002Date of Patent: May 25, 2004Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Julian M Reed, Paul Hodgson, David Geary, Ian G Martindale
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Publication number: 20030138316Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.Type: ApplicationFiled: October 29, 2002Publication date: July 24, 2003Applicant: Rolls-Royce plcInventors: Sivasubramaniam K. Sathianathan, Julian M. Reed, Paul Hodgson, David Geary, Ian G. Martindale
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Patent number: 6575694Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.Type: GrantFiled: August 8, 2001Date of Patent: June 10, 2003Assignee: Rolls-Royce plcInventors: Ewan F Thompson, Ian G Martindale, David S Knott, Kenneth F Udall, David Geary, Julian M Reed, Sivasubramaniam K Sathianathan
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Patent number: 6543991Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.Type: GrantFiled: March 23, 2001Date of Patent: April 8, 2003Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Julian M Reed, Paul Hodgson, David Geary, Ian G Martindale
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Publication number: 20030014964Abstract: A joint assembly for limiting an extension of the joint in the direction of a load path derived from an impact comprising a first member having a portion and a second member having a portion, the portions overlapping one another and arranged generally parallel to one another and secured together via securing means disposed through corresponding holes defined therein. One of the overlapping portions further defines, sequentially in the direction of extension, a shear neck, a pocket and a catcher portion. In the event of a worst-case impact load the securing means shears through the shear neck and the pocket and is arrested by the catcher portion, thereby the extension of the joint assembly is limited and the joint assembly remains integral.Type: ApplicationFiled: July 9, 2002Publication date: January 23, 2003Inventors: Sivasubramaniam K. Sathianathan, Peter E. Farrington, Ian G. Martindale, Caroline McLachlan, Stephen J. Booth, Duncan Auterson, David S. Yazdani
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Publication number: 20020164244Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54) and a downstream portion (60). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54) and the downstream portion (60). The downstream portion (60) has impact protection means (64B) located on its inner surface (62) to protect the downstream portion (60) of the containment casing (40). The impact protection means (64) comprises a plurality of radially inwardly and circumferentially extending ribs (80) on the inner surface (62) of the downstream portion (60) to act as spacer between an inner portion of a detached fan blade (34) and the downstream portion (60).Type: ApplicationFiled: March 18, 2002Publication date: November 7, 2002Inventors: Sivasubramaniam K. Sathianathan, Stephen J. Booth, Ian G. Martindale
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Patent number: 6394746Abstract: A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, first metal casing (40) and a plurality of generally cylindrical, or frustoconical axially spaced second metal casing is (54, 56 & 58). The second metal casings (54, 56, 58) surrounded and abut the first metal casing (40). The first metal casing (40) is relatively hard and tough to contain a fan blade (34). The second metal casings (54, 56, 58 are relatively soft and lightweight to stiffen the first metal casing (40) and fan blade containment regions (A, B & C). The second metal casing (54, 56, 58) are arranged coaxially with the first metal casing (40). One of the second metal casing means (56) is in a plane (Y) containing the fan blades (34) of the gas turbine engine (10). The first metal casing (40) comprises steel and the second metal casing is (54, 56, 58) comprise aluminum. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).Type: GrantFiled: September 18, 2000Date of Patent: May 28, 2002Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Ian G Martindale, Michael R Lawson
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Patent number: 6371721Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular hook (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular hook (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). The metal casing (40) has a containment portion (A) downstream of the annular hook (54) and substantially in the plane of the leading edge of the tip (37) of the fan blade (34). The containment portion (A) of the casing (40) has a greater diameter than the diameter of the casing (40) at the annular hook (54) to restrain upstream movement of a detached fan blade (34).Type: GrantFiled: September 18, 2000Date of Patent: April 16, 2002Assignee: Rolls-Royce plcInventors: Sivasubramaniam K Sathianathan, Ian G Martindale, David Geary, Julian M Reed
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Publication number: 20020004005Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.Type: ApplicationFiled: March 23, 2001Publication date: January 10, 2002Inventors: Sivasubramaniam K. Sathianathan, Julian M. Reed, Paul Hodgson, David Geary, Ian G. Martindale