Patents by Inventor Nicholas John Bloom
Nicholas John Bloom 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).
-
Patent number: 11898494Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: GrantFiled: October 15, 2021Date of Patent: February 13, 2024Assignee: General Electric CompanyInventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
-
Patent number: 11859819Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.Type: GrantFiled: October 15, 2021Date of Patent: January 2, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Ryan Christopher Jones, Shai Birmaher, Nicholas John Bloom, Daniel J. Kirtley, Gerardo Antonio Salazar Lois, Anquan Wang, Trevor James Hahm
-
Patent number: 11828466Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.Type: GrantFiled: October 12, 2021Date of Patent: November 28, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Gerardo Antonio Salazar Lois, Daniel J. Kirtley, Nicholas John Bloom, Shai Birmaher, Ryan Christopher Jones
-
Publication number: 20230119008Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.Type: ApplicationFiled: October 15, 2021Publication date: April 20, 2023Inventors: Ryan Christopher Jones, Shai Birmaher, Nicholas John Bloom, Daniel J. Kirtley, Gerardo Antonio Salazar Lois, Anquan Wang, Trevor James Hahm
-
Publication number: 20230114116Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.Type: ApplicationFiled: October 12, 2021Publication date: April 13, 2023Inventors: Gerardo Antonio Salazar Lois, Daniel J. Kirtley, Nicholas John Bloom, Shai Birmaher, Ryan Christopher Jones
-
Publication number: 20230112757Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome including a swirler opening therethrough with a flare interface surface surrounding the swirler opening, a swirler assembly including (a) a secondary swirler having a threaded flare attachment portion, and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flare interface surface of the CMC dome, and a swirler-dome attachment member. The flare is connected to the secondary swirler via the threaded flare attachment portion and the threaded secondary swirler attachment portion, and the swirler-dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flare interface surface so as to connect the CMC dome and the swirler assembly.Type: ApplicationFiled: October 12, 2021Publication date: April 13, 2023Inventors: Gerardo Antonio Salazar Lois, Nicholas John Bloom, Daniel J. Kirtley, Shai Birmaher, Ryan Christopher Jones
-
Publication number: 20220333778Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: ApplicationFiled: July 1, 2022Publication date: October 20, 2022Inventors: Michael Alan Stieg, Nicholas John Bloom
-
Patent number: 11454128Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.Type: GrantFiled: August 6, 2018Date of Patent: September 27, 2022Assignee: General Electric CompanyInventors: Mark Anthony Holleran, Matthew Mark Weaver, Darrell Glenn Senile, Nicholas John Bloom
-
Publication number: 20220275730Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.Type: ApplicationFiled: May 16, 2022Publication date: September 1, 2022Inventors: Mark Anthony Holleran, Matthew Mark Weaver, Darrell Glenn Senile, Nicholas John Bloom
-
Patent number: 11402097Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: GrantFiled: January 3, 2018Date of Patent: August 2, 2022Assignee: General Electric CompanyInventors: Michael Alan Stieg, Nicholas John Bloom
-
Publication number: 20220205392Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: ApplicationFiled: October 15, 2021Publication date: June 30, 2022Inventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
-
Patent number: 11149646Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: GrantFiled: September 2, 2015Date of Patent: October 19, 2021Assignee: General Electric CompanyInventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
-
Patent number: 10801729Abstract: A combustor for a gas turbine engine is provided, which includes: a CMC liner having a forward end and an aft end; an annular dome comprising a metal and defining an annular slot within its end defined between an outer arm and an inner arm; a feather seal extending from an annularly exterior surface of the annular dome to an annularly exterior surface of the liner; and a plurality of pin members. The forward end of the liner defines a plurality of fingers and a plurality of axial slots, and is fitted between the outer arm and the inner arm within the annular slot. Each pin member extending through an aperture in the feather seal, through an aperture in the outer arm of the annular dome, through an opening defined by the liner, and through an aperture in the inner arm of the annular dome.Type: GrantFiled: July 6, 2015Date of Patent: October 13, 2020Assignee: General Electric CompanyInventor: Nicholas John Bloom
-
Patent number: 10737986Abstract: Methods for repairing composite cylindrical components are provided. One exemplary method for repairing a cylindrical component defining an axial direction, a radial direction, and a circumferential direction includes removing a damaged region of the cylindrical component. A flange extending from a cylindrical body of the cylindrical component is included in the damaged region. One or more arc segments that extend along the circumferential direction are connected with the existing cylindrical component. At least one of the arc segments includes a prefabricated flange. One or more plies are laid up to connect the arc segments with the existing cylindrical component to repair the damaged region of the cylindrical body and the prefabricated flange formed integrally with one of the arc segments replaces the damaged portion of the flange. Repaired cylindrical components are also provided.Type: GrantFiled: September 19, 2017Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Herbert Chidsey Roberts, Glenn Curtis Taxacher, Nicholas John Bloom, Patrick Wayne Hollingsworth
-
Publication number: 20200158341Abstract: A combustor for a gas turbine engine is provided, which includes: a CMC liner having a forward end and an aft end; an annular dome comprising a metal and defining an annular slot within its end defined between an outer arm and an inner arm; a feather seal extending from an annularly exterior surface of the annular dome to an annularly exterior surface of the liner; and a plurality of pin members. The forward end of the liner defines a plurality of fingers and a plurality of axial slots, and is fitted between the outer arm and the inner arm within the annular slot. Each pin member extending through an aperture in the feather seal, through an aperture in the outer arm of the annular dome, through an opening defined by the liner, and through an aperture in the inner arm of the annular dome.Type: ApplicationFiled: July 6, 2015Publication date: May 21, 2020Inventor: Nicholas John BLOOM
-
Publication number: 20200040749Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.Type: ApplicationFiled: August 6, 2018Publication date: February 6, 2020Inventors: Mark Anthony Holleran, Matthew Mark Weaver, Darrell Glenn Senile, Nicholas John Bloom
-
Publication number: 20190203940Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one aspect, the forward end of the liner defines blind warming openings that allow a warming airflow to actively warm the forward end during transient operation of the engine. In another aspect, the dome defines a plurality of impingement openings that allow a warming airflow to impinge on the forward end to actively warm the liner during transient operation of the engine. In another aspect, a grommet coupling a pin with the liner defines a plurality of warming passages that allow a warming airflow to flow therethrough to warm the forward end of the liner during transient engine operation.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom, Brett Joseph Geiser
-
Publication number: 20190203611Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. At least a portion of the forward end is received within the slot of the dome. The forward end of the liner defines a plurality of warming holes that allow for a warming airflow to flow therethrough to warm the forward end at a faster rate during transient operating conditions of the engine thereby reducing transient stresses and increasing liner durability.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom, Eric Ryan Newburn, Brett Joseph Geiser
-
Publication number: 20190203939Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom
-
Publication number: 20190137101Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.Type: ApplicationFiled: December 21, 2018Publication date: May 9, 2019Inventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton