Patents by Inventor Takeo Oda
Takeo Oda 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: 9664391Abstract: An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.Type: GrantFiled: November 27, 2013Date of Patent: May 30, 2017Assignees: KAWASAKI JUKOGYO KABUSHIKI KAISHA, JAPAN AEROSPACE EXPLORATION AGENCYInventors: Masayoshi Kobayashi, Takeo Oda, Ryusuke Matsuyama, Atsushi Horikawa, Hitoshi Fujiwara
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Patent number: 9638423Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.Type: GrantFiled: February 12, 2015Date of Patent: May 2, 2017Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Masahiro Ogata, Takeo Oda, Yasuhiro Kinoshita
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Patent number: 9429324Abstract: A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel.Type: GrantFiled: May 31, 2012Date of Patent: August 30, 2016Assignees: Kawasaki Jukogyo Kabushiki Kaisha, Japan Aerospace Exploration AgencyInventors: Ryusuke Matsuyama, Masayoshi Kobayashi, Takeo Oda, Atsushi Horikawa, Shigeru Hayashi, Kazuo Shimodaira, Kazuaki Matsuura, Hideshi Yamada, Youji Kurosawa, Hitoshi Fujiwara
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Patent number: 9400113Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.Type: GrantFiled: June 12, 2014Date of Patent: July 26, 2016Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Masahiro Ogata, Takeo Oda, Yasuhiro Kinoshita
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Patent number: 9366442Abstract: A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the pilot injector includes: a center nozzle configured to eject air jet flowing straight in an axial direction on a central axis of the pilot injector; an inside swirler provided on a radially outer side of the center nozzle and configured to cause inflow air to swirl around the central axis; and a pilot fuel injecting portion configured to inject the fuel from between the center nozzle and the inside swirler to air flow in the center nozzle.Type: GrantFiled: May 31, 2012Date of Patent: June 14, 2016Assignees: Kawasaki Jukogyo Kabushiki Kaisha, Japan Aerospace Exploration AgencyInventors: Ryusuke Matsuyama, Masayoshi Kobayashi, Takeo Oda, Atsushi Horikawa, Shigeru Hayashi, Kazuo Shimodaira, Kazuaki Matsuura, Hideshi Yamada, Youji Kurosawa, Hitoshi Fujiwara
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Publication number: 20160033131Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.Type: ApplicationFiled: June 12, 2014Publication date: February 4, 2016Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Masahiro OGATA, Takeo ODA, Yasuhiro KINOSHITA
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Publication number: 20150362194Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.Type: ApplicationFiled: February 12, 2015Publication date: December 17, 2015Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Masahiro OGATA, Takeo ODA, Yasuhiro KINOSHITA
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Publication number: 20150275755Abstract: A multi-fuel-capable gas turbine combustor is provided which is able to sufficiently utilize various fuels having a characteristic deviating from a premixing characteristic range suitable for generating a premixed gas, even while maintaining favorable low-emission performance by premixed combustion. The gas turbine combustor includes: a main burner configured to supply a premixed gas containing a first fuel for premixing, to a first combustion region within a combustion chamber to cause premixed combustion; and a supplemental burner configured to supply a second fuel for reheating having a different composition from that of the first fuel, to a second combustion region at a location downstream of the first combustion region within the combustion chamber, to cause diffusion combustion. The first fuel has a premixing characteristic range suitable for generating a premixed gas. The second fuel has a characteristic deviating from the premixing characteristic range.Type: ApplicationFiled: June 11, 2015Publication date: October 1, 2015Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Masahiro OGATA, Takeo ODA, Yasuhiro KINOSHITA
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Publication number: 20140182294Abstract: A gas turbine combustor includes a pilot burner, provided at a top portion of a combustion liner having a combustion chamber defined therein, and a main burner of a premixing type disposed adjacent an outer periphery thereof. The pilot burner is provided with an inflow passage, provided in an upstream end portion to allow the compressed air from a radially outer area into a radially inner area, a plurality of fuel supply holes for injecting the fuel into the inflow passage in a direction perpendicular to the flow of the compressed air, a premixing passage for guiding the air-fuel mixture from the inflow passage in an axially downstream direction while the compressed air and the fuel are mixed together, and a plurality of premixed air-fuel mixture injection holes for injecting the premixed air-fuel mixture from the premixing passage into the combustion chamber.Type: ApplicationFiled: March 4, 2014Publication date: July 3, 2014Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Kiyoshi MATSUMOTO, Takeo ODA
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Publication number: 20140083105Abstract: An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.Type: ApplicationFiled: November 27, 2013Publication date: March 27, 2014Applicants: Japan Aerospace Exploration Agency, Kawasaki Jukogyo Kabushiki KaishaInventors: Masayoshi KOBAYASHI, Takeo ODA, Ryusuke MATSUYAMA, Atsushi HORIKAWA, Hitoshi FUJIWARA
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Patent number: 8656721Abstract: This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage.Type: GrantFiled: March 11, 2010Date of Patent: February 25, 2014Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Kiyoshi Matsumoto, Takeo Oda
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Patent number: 8572977Abstract: The present combustor of gas turbine engine includes: a fuel injection unit including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage and a main fuel passage to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure.Type: GrantFiled: March 13, 2008Date of Patent: November 5, 2013Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Takeo Oda, Hideki Ogata
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Patent number: 8511097Abstract: A gas turbine combustor burns a fuel mixture at a high combustion efficiency and a low NOx emission, is simple in construction and exercises improved ignition performance, and an ignition method can efficiently igniting a fuel mixture in the gas turbine combustor. A gas turbine combustor provided with fuel nozzles each having a pilot fuel injection nozzle and a main fuel injection nozzle, and fuel nozzles each having a pilot fuel injection nozzle and a main fuel injection nozzle. The fuel nozzle disposed close to an igniter is provided with a local fuel injection port through which fuel is jetted out from a predetermined position in an air passage in the main fuel injection nozzle to create a combustible fuel mixture zone in the vicinity of the igniter at least while the igniter is in an ignition operation.Type: GrantFiled: March 15, 2006Date of Patent: August 20, 2013Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Masayoshi Kobayashi, Hiroyuki Ninomiya, Takeo Oda
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Publication number: 20120304649Abstract: A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel.Type: ApplicationFiled: May 31, 2012Publication date: December 6, 2012Applicants: JAPAN AEROSPACE EXPLORATION AGENCY, KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Ryusuke MATSUYAMA, Masayoshi KOBAYASHI, Takeo ODA, Atsushi HORIKAWA, Shigeru HAYASHI, Kazuo SHIMODAIRA, Kazuaki MATSUURA, Hideshi YAMADA, Youji KUROSAWA, Hitoshi FUJIWARA
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Publication number: 20120305673Abstract: A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the pilot injector includes: a center nozzle configured to eject air jet flowing straight in an axial direction on a central axis of the pilot injector; an inside swirler provided on a radially outer side of the center nozzle and configured to cause inflow air to swirl around the central axis; and a pilot fuel injecting portion configured to inject the fuel from between the center nozzle and the inside swirler to air flow in the center nozzle.Type: ApplicationFiled: May 31, 2012Publication date: December 6, 2012Applicants: JAPAN AEROSPACE EXPLORATION AGENCY, KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Ryusuke Matsuyama, Masayoshi Kobayashi, Takeo Oda, Atsushi Horikawa, Shigeru Hayashi, Kazuo Shimodaira, Kazuaki Matsuura, Hideshi Yamada, Youji Kurosawa, Hitoshi Fujiwara
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Patent number: 8225612Abstract: A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber.Type: GrantFiled: October 7, 2010Date of Patent: July 24, 2012Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Takeo Oda, Hiroyuki Ninomiya, Hideki Ogata
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Patent number: 8001786Abstract: A combustor of gas turbine engine, including: a fuel spray portion that sprays fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion that atomizes the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a spreading trumpet-like shape and diffuses the fuel and the air; a pre-mixture supply portion that supplies a pre-mixture gas including the fuel and air to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion to surround the fuel spray portion; and a fuel diffusion restraining member disposed on an inner circumferential face of the diffusion passage portion for restraining a diffusion of injected fuel by separating a stream of the injected fuel away from the inner circumferential face.Type: GrantFiled: February 11, 2008Date of Patent: August 23, 2011Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Takeo Oda, Atsushi Horikawa, Hideki Ogata
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Patent number: 7921650Abstract: A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber.Type: GrantFiled: December 12, 2006Date of Patent: April 12, 2011Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Takeo Oda, Hiroyuki Ninomiya, Hideki Ogata
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Publication number: 20110016868Abstract: A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber.Type: ApplicationFiled: October 7, 2010Publication date: January 27, 2011Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Takeo ODA, Hiroyuki NINOMIYA, Hideki OGATA
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Publication number: 20100229557Abstract: This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage.Type: ApplicationFiled: March 11, 2010Publication date: September 16, 2010Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHAInventors: Kiyoshi Matsumoto, Takeo Oda