A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first an
A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first and second sides. The pre-orifice is configured to be removed through the end cover from the second side.
대표청구항▼
1. A system comprising: an end cover of a multi-tube fuel nozzle, wherein the end cover comprises: a first side;a second side disposed opposite the first side;a plurality of fuel injectors disposed on the first side;a pre-orifice cavity extending through the end cover from the first side to the seco
1. A system comprising: an end cover of a multi-tube fuel nozzle, wherein the end cover comprises: a first side;a second side disposed opposite the first side;a plurality of fuel injectors disposed on the first side;a pre-orifice cavity extending through the end cover from the first side to the second side; andat least one pre-orifice conduit disposed within the pre-orifice cavity, wherein the at least one pre-orifice conduit comprises: a longitudinal wall having a first end portion and a second end portion, the first end portion disposed to the second side within the end cover and the second end portion extends through and beyond the first side,a plurality of apertures disposed on the longitudinal wall of the at least one pre-orifice conduit on the second end portion to deliver fuel to a fuel plenum, and wherein the at least one pre-orifice conduit is configured to be removed through the end cover from the second side. 2. The system of claim 1, comprising a cover different from the end cover, the cover is disposed on the second side of the end cover over the pre-orifice cavity to enclose the at least one pre-orifice conduit within the end cover. 3. The system of claim 1, wherein the pre-orifice conduit is breech-loaded through the second side into the end cover. 4. The system of claim 1, wherein the end cover comprises the fuel plenum disposed within the end cover between the first and second sides, the second end portion of the at least one pre-orifice conduit is disposed within the fuel plenum, and the fuel plenum is in fluid communication with at least two or more fuel injectors of the plurality of fuel injectors. 5. The system of claim 1, wherein the system comprises a gas turbine engine, a combustor, the multi-tube fuel nozzle, or a combination thereof, having the end cover. 6. The system of claim 2, wherein the cover is configured to be removed to enable removal of the at least one pre orifice conduit through the end cover from the second side. 7. A system comprising: an end cover of a combustor for a gas turbine engine, wherein the end cover comprises: a first side;a second side disposed opposite the first side, wherein the first side is configured to reach a higher temperature relative to the second side during operation of the gas turbine engine;a plurality of pre-orifice cavities extending through the end cover from the first side to the second side; anda plurality of pre-orifice conduits disposed within respective said pre-orifice cavities within the end cover between the first and second sides, wherein each of the plurality of said pre-orifice conduits comprises: a respective longitudinal wall, wherein each of the respective longitudinal wall having a respective first end portion and a respective second end portion,a plurality of apertures disposed on each of the respective second end portion to deliver fuel to a fuel plenum, andwherein the each of the plurality of said pre-orifice conduits is configured to be removed through the end cover from the second side; anda plurality of covers, wherein each cover is different from the end cover and is disposed on the second side of the end cover over one of the respective pre-orifice cavities to enclose a respective pre-orifice conduit of the each of the plurality of said pre-orifice conduits within the end cover. 8. The system of claim 7, wherein each of the cover is configured to be removed to enable removal of the respective pre-orifice conduit through the end cover from the second side. 9. The system of claim 7, wherein the end cover comprises a plurality of fuel injectors disposed on the first side. 10. The system of claim 7, wherein the each of the plurality of said pre-orifice conduits is breech-loaded through the second side into the end cover. 11. The system of claim 9, wherein the end cover comprises a plurality of fuel plenums disposed within the end cover between the first and second sides, and each of the fuel plenum of the plurality of fuel plenums is in fluid communication with at least one or more fuel injectors of the plurality of fuel injectors. 12. The system of claim 11, wherein a portion of a portion of the each of the plurality of said pre-orifice conduits extends into a respective fuel plenum of the plurality of fuel plenums. 13. The system of claim 12, wherein the each of the plurality of said pre-orifice conduits is configured to provide fuel to the respective fuel plenum of the plurality of fuel plenums via a plurality of apertures disposed on the longitudinal wall of the respective pre-orifice conduit.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (72)
Johnson, Thomas Edward; Ziminsky, Willy Steve; Berry, Jonathan Dwight, Apparatus and method for mixing fuel in a gas turbine nozzle.
Angel Paul R. (Fairfield OH) Caldwell James M. (Alexandria KY) Heberling Paul V. (Cincinnati OH) Dean Anthony J. (Scotia NY) Joshi Narendra D. (Cincinnati OH), Dual fuel mixer for gas turbine combustor.
Bailey, Donald Mark; Simmons, Scott Robert; Huffman, Marcus Byron, Fuel nozzle assembly that exhibits a frequency different from a natural operating frequency of a gas turbine engine and method of assembling the same.
Mandai Shigemi,JPX ; Kawabata Hitoshi,JPX ; Nishida Koichi,JPX, Gas turbine combustor having multiple burner groups and independently operable pilot fuel injection systems.
Smith, Craig F.; Alholm, Hannes A.; Eastwood, Jonathan J.; Duhamel, Dennis J.; Burns, David A.; Barnett, Jr., Claude I.; Danburg, Randy J.; Melman, Jeffrey D.; Wiley, David R.; Pacheco-Tougas, Monica, Gas turbine combustor liner cap assembly.
Bailey, Donald Mark; Berry, Jonathan Dwight; Flamand, Luis Manuel; Kim, Kwanwoo; Melton, Patrick Benedict; Rohrssen, Robert Joseph; Vanselow, John Drake, Gas turbine engine combustor with lobed, three dimensional contouring.
Davis, Jr., Lewis Berkley; Johnson, Thomas Edward; Stewart, Jason Thurman, Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages.
Amond, III,Thomas Charles; Crawley,Bradley Donald; Chandrashekar,Natesh; Nagarajan,Balan; Feigl Varela,Rebecca Arlene, Methods and apparatus for low emission gas turbine energy generation.
Davis, Jr., Lewis Berkley; Han, Fei; Srinivasan, Shiva; Singh, Kapil Kumar; Kim, Kwanwoo; Narra, Venkateswarlu, Resonator assembly for mitigating dynamics in gas turbines.
Richard Sterling Tuthill ; William Theodore Bechtel, II ; Jeffrey Arthur Benoit ; Stephen Hugh Black ; Robert James Bland ; Guy Wayne DeLeonardo ; Stefan Martin Meyer ; Joseph Charles Taura ;, Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.