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公开(公告)号：EP4450775A1
公开(公告)日：2024-10-23
申请号：EP24171757.8
申请日：2024-04-22
申请人： RTX Corporation
发明人： GOYETTE, Scott , SHAW, Janet , HAGEN, Gregory S. , LINCOLN, David L. , CHAUDHRY, Zaffir A. , LEE, Jeremiah C. , SETO, Danbing
摘要： An assembly (70, 72) for an aircraft propulsion system (20) includes a propulsor section (28), an imaging device (98), a plurality of light sources (110), and a controller (96). The propulsor section (28) includes a propulsor (40). The propulsor (40) includes a plurality of propulsor blades (46). The imaging device (98) is disposed in the propulsor section (28). The imaging device (98) includes a camera (108). The plurality of light sources (110) are disposed in the propulsor section (28). The controller (96) includes a processor (102) in communication with a non-transitory memory (104) storing instructions, which instructions when executed by the processor (102), cause the processor (102) to: control the plurality of light sources (110) to direct light (114) to the plurality of propulsor blades (46), control the camera (108) to capture image data (146) of each propulsor blade (148) of the plurality of propulsor blades (46), and identify a presence or an absence of damage for each propulsor blade (148) of the plurality of propulsor blades (46) using the image data (146).
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公开(公告)号：EP4450770A2
公开(公告)日：2024-10-23
申请号：EP24171080.5
申请日：2024-04-18
申请人： RTX Corporation
发明人： GOYETTE, Scott , HAGEN, Gregory S. , CHAUDHRY, Zaffir A. , ATTRIDGE, Paul , SHAW, Janet , LINCOLN, David L. , KING, Jeffrey P.
摘要： An assembly for an aircraft propulsion system (20) includes a propulsor (40) and an imaging assembly (26). The propulsor (40) includes a propulsor disk (44), a plurality of propulsor blades (46), and a nose cone (48). The plurality of propulsor blades (46) are circumferentially distributed about the propulsor disk (44). Each propulsor blade of the plurality of propulsor blades (46) extends radially between and to a root end (50) and a tip end (52). The root end (50) is disposed at the propulsor disk (44). The propulsor disk (44) and the plurality of propulsor blades (46) are configured to rotate about the rotational axis (38). The nose cone (48) is disposed axially adjacent the propulsor disk (44). The imaging assembly (26) includes an imaging device (98) disposed on the nose cone (48). The imaging device (98) includes a camera (108). The camera (108) is configured to capture image data of each propulsor blade of the plurality of propulsor blades (46) as the plurality of propulsor blades (46) rotate about the rotational axis (38).
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公开(公告)号：EP4450771A2
公开(公告)日：2024-10-23
申请号：EP24171103.5
申请日：2024-04-18
申请人： RTX Corporation
发明人： GOYETTE, Scott , SHAW, Janet , HAGEN, Gregory S. , LINCOLN, David L. , CHAUDHRY, Zaffir A. , KING, Jeffrey P.
摘要： An inspection system (88) for rotating fan rotor blades (58) in a gas turbine engine (20) is provided. The system includes a plurality of cameras (100) and lids (108), and a cleaning system (94). The cameras (100) are each controllable to capture an image of a leading edge (62) of a fan rotor blade (58) and produce signals representative thereof. Each camera (100) is mounted to a static structure (54, 74) disposed forward of the fan rotor blade stage (52). The lids (108) are attached to the static structure and are selectively movable between closed and open positions. In the closed position at least one camera (100) is enclosed. In the open position the camera (100) is at least partially exposed and has a field of view of the rotating fan rotor blades (58). The cleaning system (94) is controllable to selectively produce a body of fluid relative to the at least one camera (100) when the respective lid (108) is in the open position.
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4.发明公开
公开(公告)号：EP4421732A2
公开(公告)日：2024-08-28
申请号：EP24155616.6
申请日：2024-02-02
申请人： RTX Corporation
发明人： LEE, Jeremiah C. , ATTRIDGE, Paul , CHAUDHRY, Zaffir A. , GOYETTE, Scott , HAGEN, Gregory S. , LINCOLN, David L. , LORE, Kin Gwn
IPC分类号： G06T7/00
摘要： Methods of inspecting fan blades (70) of a gas turbine engine (20) for abnormalities are disclosed. One method utilizes a neural network (108) to determine whether a photographic image (114) of at least one fan blade (70) depicts an abnormality of the at least one fan blade (70). Another method uses a dimensional reduction technique on one or more first photographic images (110) that depict at least one first fan blade (70) to obtain basis vectors, utilizes the basis vectors to obtain a reconstructed version of a second photographic image (114) that depicts at least one second fan blade (70), and determines whether the at least one second fan blade (70) includes an abnormality based on a difference between the second photographic image (114) and the reconstructed version of the second photographic image (114). Another method determines whether a fan blade (70) includes an abnormality based on contrast differences between adjacent areas of an image.
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公开(公告)号：EP4450957A1
公开(公告)日：2024-10-23
申请号：EP24171094.6
申请日：2024-04-18
申请人： RTX Corporation
发明人： GOYETTE, Scott , SHAW, Janet , HAGEN, Gregory S. , ATTRIDGE, Paul , CHAUDHRY, Zaffir A. , LINCOLN, David L. , KING, Jeffrey P.
IPC分类号： G01N21/954
摘要： An inspection system (88) for rotating fan rotor blades (58) is provided that includes a plurality of cameras (100) and light sources (92) and a system controller (98). The cameras (100) are controllable to capture an image of a leading edge (62) of a fan rotor blade (58) and produce signals representative of the captured image. Each respective camera (100) is mounted with an inlet guide vane (74) disposed forward of the fan rotor blade stage (52). The light sources (92) are each associated with a respective camera (100). The system controller (98) is in communication with the cameras (100), the light sources (92), and a non-transitory memory storing instructions. The instructions when executed cause the system controller (98) to: control the light sources (92) to selectively illuminate the fan rotor blades (58), and control the cameras (100) to image respective fan rotor blades (58) and produce signals representative thereof, and provide inspection information representative of the leading edge (62) of respective fan rotor blades (58).
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公开(公告)号：EP4450774A2
公开(公告)日：2024-10-23
申请号：EP24171458.3
申请日：2024-04-19
申请人： RTX Corporation
发明人： GOYETTE, Scott , SHAW, Janet , HAGEN, Gregory S. , LINCOLN, David L. , CHAUDHRY, Zaffir A. , SETO, Danbing
摘要： An assembly (70, 72) for an aircraft propulsion system (20) includes a propulsor section (28) for the aircraft propulsion system (20), a plurality of imaging devices (98), and a controller (96). The propulsor section (28) includes a propulsor (40). The propulsor (40) includes a plurality of propulsor blades (46). The plurality of imaging devices (98) are mounted in the propulsor section (28). Each imaging device (98) includes a camera (108). The controller (96) includes a processor (102) in communication with a non-transitory memory (104) storing instructions, which instructions when executed by the processor (102), cause the processor (102) to: control the camera (108) of each imaging device (98) of the plurality of imaging devices (98) to capture image data (146) of each propulsor blade (148) of the plurality of propulsor blades (46) and identify a presence or an absence of damage for each propulsor blade (148) of the plurality of propulsor blades (46) using the image data (146) from the camera (108) of two or more imaging devices (98) of the plurality of imaging devices (98).
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公开(公告)号：EP4450773A2
公开(公告)日：2024-10-23
申请号：EP24171134.0
申请日：2024-04-18
申请人： RTX Corporation
发明人： HAGEN, Gregory S. , ATTRIDGE, Paul , LINCOLN, David L. , CHAUDHRY, Zaffir A. , GOYETTE, Scott , SHAW, Janet , KING, Jeffrey P.
摘要： An assembly for an aircraft propulsion system (20) includes a propulsor section (28) and an imaging device (98). The propulsor section (28) includes a propulsor (40) and a structural body (116). The propulsor (40) includes a plurality of propulsor blades (46). The structural body (116) forms an outer air flow surface (118) forming a portion of an air flow path through the propulsor section (28). The imaging device (98) includes a housing (122) and a camera (108). The housing (122) includes a housing body (124) and a cover (126). The housing body (124) is mounted in the structural body (116). The housing body (124) forms a cavity (134) and an opening (136) of the cavity (134). The cover (126) is pivotable between a stowed position and a deployed position. The camera (108) is disposed in the cavity (134) with the cover (126) positioned in the stowed position. The camera (108) is configured to capture image data of each propulsor blade of the plurality of propulsor blades (46) with the cover (126) positioned in the deployed position.
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公开(公告)号：EP4450772A1
公开(公告)日：2024-10-23
申请号：EP24171118.3
申请日：2024-04-18
申请人： RTX Corporation
发明人： GOYETTE, Scott , SHAW, Janet , HAGEN, Gregory S. , CHAUDHRY, Zaffir A. , LINCOLN, David L. , KING, Jeffrey P.
摘要： An inspection system (88) for fan rotor blades (58) in a gas turbine engine (20) is provided. The gas turbine engine (20) has a sensor that provides a fan rotor stage (52) speed signal. The system includes a plurality of cameras (100) and light sources (92) and a system controller (98). The cameras (100) are controllable to image a leading edge (62) of a fan rotor blade (58). Each respective camera (100) and light source (92) is mounted with a static structure (54, 74) disposed forward of the fan rotor blade stage (52). The system controller (98) is in communication with stored instructions that when executed cause the system controller (98) to monitor the speed of the fan rotor stage (52) during an engine (20) shutdown; upon the fan rotor stage (52) speed reaching a first value, control the light sources (92) to selectively illuminate the fan rotor blades (58), and control the cameras (100) to image the fan rotor blades (58), and provide inspection information using signals representative of the captured images.
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