Patents by Inventor Ashok Babu Saya
Ashok Babu Saya 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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Publication number: 20240077018Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure and a nozzle. The nacelle inlet structure extends circumferentially about an axial centerline. The nacelle inlet structure includes an inlet lip, a bulkhead and an internal cavity formed by and axially between the inlet lip and the bulkhead. The nozzle is configured to direct gas into the internal cavity axially towards the bulkhead.Type: ApplicationFiled: September 1, 2023Publication date: March 7, 2024Inventors: PramodaKumar Nayak, Ashok Babu Saya
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Patent number: 11859578Abstract: A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.Type: GrantFiled: April 8, 2022Date of Patent: January 2, 2024Assignee: Rohr, Inc.Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Patent number: 11788488Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.Type: GrantFiled: August 18, 2021Date of Patent: October 17, 2023Assignee: ROHR, INC.Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Patent number: 11613373Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a nacelle inlet structure with an internal cavity. The assembly also includes a nozzle configured to direct fluid into the internal cavity through a plurality of ports that include one or more first ports and at least one second port. The nozzle includes a trunk conduit, a first branch conduit and a second branch conduit. The first branch conduit and the second branch conduit are fluidly coupled in parallel to the trunk conduit. The first branch conduit includes the first port(s). The second branch conduit includes the second port.Type: GrantFiled: March 12, 2021Date of Patent: March 28, 2023Assignee: Rohr, Inc.Inventors: Radhakrishna Chilukuri, Yuvaraj Patil, Ashok Babu Saya, Vanukuri Venkatareddy
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Patent number: 11566583Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.Type: GrantFiled: February 9, 2022Date of Patent: January 31, 2023Assignee: Rohr, Inc.Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Publication number: 20220325679Abstract: A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.Type: ApplicationFiled: April 8, 2022Publication date: October 13, 2022Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Publication number: 20220268237Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.Type: ApplicationFiled: February 9, 2022Publication date: August 25, 2022Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Patent number: 11408342Abstract: An injector head for an anti-icing system may comprise a body configured to receive a pressurized gas, wherein the body is configured to provide the pressurized gas through a bulkhead into an interior volume of a D-duct, a first nozzle configured to generate a first flow of a first portion of the pressurized gas, a second nozzle configured to generate a second flow of a second portion of the pressurized gas, and a third nozzle configured to generate a third flow of a third portion of the pressurized gas, wherein the first nozzle is located at a distal end of the body relative to the bulkhead, and wherein a first hydraulic diameter of the first nozzle is less than each of a second hydraulic diameter of the second nozzle and a third hydraulic diameter of the third nozzle.Type: GrantFiled: December 28, 2020Date of Patent: August 9, 2022Assignee: ROHR, INC.Inventors: Yuvaraj Patil, Radhakrishna Chilukuri, Vanukuri Venkatareddy, Ashok Babu Saya
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Publication number: 20220112864Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.Type: ApplicationFiled: August 18, 2021Publication date: April 14, 2022Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
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Publication number: 20210284351Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a nacelle inlet structure with an internal cavity. The assembly also includes a nozzle configured to direct fluid into the internal cavity through a plurality of ports that include one or more first ports and at least one second port. The nozzle includes a trunk conduit, a first branch conduit and a second branch conduit. The first branch conduit and the second branch conduit are fluidly coupled in parallel to the trunk conduit. The first branch conduit includes the first port(s). The second branch conduit includes the second port.Type: ApplicationFiled: March 12, 2021Publication date: September 16, 2021Inventors: Radhakrishna Chilukuri, Yuvaraj Patil, Ashok Babu Saya, Vanukuri Venkatareddy
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Publication number: 20210285373Abstract: An injector head for an anti-icing system may comprise a body configured to receive a pressurized gas, wherein the body is configured to provide the pressurized gas through a bulkhead into an interior volume of a D-duct, a first nozzle configured to generate a first flow of a first portion of the pressurized gas, a second nozzle configured to generate a second flow of a second portion of the pressurized gas, and a third nozzle configured to generate a third flow of a third portion of the pressurized gas, wherein the first nozzle is located at a distal end of the body relative to the bulkhead, and wherein a first hydraulic diameter of the first nozzle is less than each of a second hydraulic diameter of the second nozzle and a third hydraulic diameter of the third nozzle.Type: ApplicationFiled: December 28, 2020Publication date: September 16, 2021Applicant: ROHR, INC.Inventors: Yuvaraj Patil, Radhakrishna Chilukuri, Vanukuri Venkatareddy, Ashok Babu Saya