Patents by Inventor Robert E. Christie
Robert E. Christie 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: 11519330Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (?p) with respect to the longitudinal centre line of the gas turbine engine.Type: GrantFiled: April 15, 2021Date of Patent: December 6, 2022Assignee: ROLLS-ROYCE plcInventors: Robert E Christie, David G MacManus, Christopher T J Sheaf
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Patent number: 11480073Abstract: A system and a method of designing a nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake, an internal surface, an azimuthal angle, and a plurality of intake lines. The air intake comprises, in flow series, an intake lip, a throat and a diffuser. The internal surface at least partially defines the air intake. The azimuthal angle is defined about the longitudinal centre line. The intake lines extend along the internal surface of the nacelle at respective values of the azimuthal angle. Each intake line axially defines the air intake along the longitudinal centre line at the respective value of the azimuthal angle. The internal surface of the nacelle between the plurality of intake lines at a given axial location along the longitudinal centre line is analytically defined by an equation.Type: GrantFiled: November 3, 2021Date of Patent: October 25, 2022Inventors: Robert E. Christie, David G. MacManus, Christopher T J Sheaf
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Patent number: 11415048Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The diffuser further includes a diffuser angle (?diff), indicating a degree of divergence of the diffuser relative to the longitudinal centre line. The diffuser angle (?diff) is from about 0 degrees to about 12 degrees.Type: GrantFiled: April 15, 2021Date of Patent: August 16, 2022Assignee: ROLLS-ROYCE plcInventors: Robert E Christie, David G MacManus, Christopher T J Sheaf
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Patent number: 11391206Abstract: An intake centre fairing for a gas turbine engine includes a body. The body includes an outer surface, an apex point and a base. The apex point is at a first end of the body and the base is at a second end of the body. The base includes a base centre. The body defines a longitudinal axis along its length, a radial direction relative to the longitudinal axis and a circumferential direction relative to the longitudinal axis. The outer surface of the body is tapered from the base to the apex point along the longitudinal axis. The apex point is radially offset relative to the base centre along the radial direction. The apex point is further circumferentially offset relative to the base centre along the circumferential direction.Type: GrantFiled: April 15, 2021Date of Patent: July 19, 2022Assignee: ROLLS-ROYCE PLCInventors: Robert E Christie, David G MacManus
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Publication number: 20220145777Abstract: A system and a method of designing a nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake, an internal surface, an azimuthal angle, and a plurality of intake lines. The air intake comprises, in flow series, an intake lip, a throat and a diffuser. The internal surface at least partially defines the air intake. The azimuthal angle is defined about the longitudinal centre line. The intake lines extend along the internal surface of the nacelle at respective values of the azimuthal angle. Each intake line axially defines the air intake along the longitudinal centre line at the respective value of the azimuthal angle. The internal surface of the nacelle between the plurality of intake lines at a given axial location along the longitudinal centre line is analytically defined by an equation.Type: ApplicationFiled: November 3, 2021Publication date: May 12, 2022Inventors: Robert E. Christie, David G. MacManus, Christopher TJ Sheaf
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Publication number: 20210355871Abstract: An intake centre fairing for a gas turbine engine includes a body. The body includes an outer surface, an apex point and a base. The apex point is at a first end of the body and the base is at a second end of the body. The base includes a base centre. The body defines a longitudinal axis along its length, a radial direction relative to the longitudinal axis and a circumferential direction relative to the longitudinal axis. The outer surface of the body is tapered from the base to the apex point along the longitudinal axis. The apex point is radially offset relative to the base centre along the radial direction. The apex point is further circumferentially offset relative to the base centre along the circumferential direction.Type: ApplicationFiled: April 15, 2021Publication date: November 18, 2021Applicant: ROLLS-ROYCE plcInventors: Robert E CHRISTIE, David G MACMANUS
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Publication number: 20210355872Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The diffuser further includes a diffuser angle (?diff), indicating a degree of divergence of the diffuser relative to the longitudinal centre line. The diffuser angle (?diff) is from about 0 degrees to about 12 degrees.Type: ApplicationFiled: April 15, 2021Publication date: November 18, 2021Applicant: ROLLS-ROYCE PLCInventors: Robert E. CHRISTIE, David G. MACMANUS, Christopher T J SHEAF
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Publication number: 20210355873Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (?p) with respect to the longitudinal centre line of the gas turbine engine.Type: ApplicationFiled: April 15, 2021Publication date: November 18, 2021Applicant: ROLLS-ROYCE plcInventors: Robert E CHRISTIE, David G MACMANUS, Christopher T J SHEAF
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Patent number: 10392971Abstract: A nacelle for a turbofan gas turbine engine, having in flow series an intake lip, a diffuser and a fan casing. The diffuser has, in flow series, a main section and a recessed section adjacent to the fan casing. A transition region, such as a step, slope or curve, is provided between the main section and the recessed section. In some arrangements the transition region may be configured to promote flow separation and the formation of a separation bubble in the recessed section.Type: GrantFiled: November 25, 2016Date of Patent: August 27, 2019Assignee: ROLLS-ROYCE plcInventors: Angus R Smith, Christopher T Sheaf, David G MacManus, Robert E Christie
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Patent number: 6894089Abstract: The present invention is directed to a composition comprising a white pigment or extended white pigment surface treated with a silane having at least one functional group capable of reacting with acids and anhydrides, at least one polymeric material and a compatibilizer. Once treated, the pigment has improved processability and dispersibility in polymeric materials. Silanizing the pigment also enhances the brightness (increase whiteness and reduce yellowness) of the pigment.Type: GrantFiled: September 9, 2003Date of Patent: May 17, 2005Assignee: General Electric CompanyInventors: Henry L. Mei, Louis M. Panzer, Eric R. Pohl, Robert E. Christie, Philbert E. Ramdatt
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Publication number: 20040048952Abstract: The present invention is directed to a composition comprising a white pigment or extended white pigment surface treated with a silane having at least one functional group capable of reacting with acids and anhydrides, at least one polymeric material and a compatibilizer. Once treated, the pigment has improved processability and dispersibility in polymeric materials. Silanizing the pigment also enhances the brightness (increase whiteness and reduce yellowness) of the pigment.Type: ApplicationFiled: September 9, 2003Publication date: March 11, 2004Inventors: Henry L. Mei, Louis M. Panzer, Eric R. Pohl, Robert E. Christie, Philbert E. Ramdatt
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Publication number: 20030027897Abstract: The present invention is directed to a composition comprising a white pigment or extended white pigment surface treated with a silane having at least one functional group capable of reacting with acids and anhydrides, at least one polymeric material and a compatibilizer. Once treated, the pigment has improved processability and dispersibility in polymeric materials. Silanizing the pigment also enhances the brightness (increase whiteness and reduce yellowness) of the pigment.Type: ApplicationFiled: April 26, 2001Publication date: February 6, 2003Inventors: Henry L. Mei, Louis M. Panzer, Eric R. Pohl, Robert E. Christie, Philbert E. Ramdatt
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Patent number: 6455158Abstract: The present invention relates to the silanization or surface treatment of minerals with alkylsilanes and alkylsilane copolymers. More specifically, the present invention relates to alkylsilane copolymers useful for surface treating pigments or fillers. The alkylsilane copolymers comprise at least two different monomers. The copolymers find particular utility for the surface treatment of white pigments, such as titanium dioxide, for improving the dispersibility and processibility of the pigments when compounded with a polymeric material, in particular, when compounded with polyolefins.Type: GrantFiled: June 16, 2000Date of Patent: September 24, 2002Assignee: Crompton CorporationInventors: Henry L. Mei, Louis M. Panzer, Herbert E. Petty, Philbert E. Ramdatt, Robert E. Christie, Juan Alfonso