RTX Corporation Patente

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A retention ring (66; 66'; 66"; 166) for a gas turbine engine (10; 20) includes, among other things, a main body (72; 172) extending in a circumferential direction about an axis (RA) to establish a continuous hoop having a first diameter (73) and a second diameter (74). The main body (72; 172) includes first and second circumferential faces (75, 76; 175, 176) along opposite sides of the main body (72; 172). The first circumferential face (75; 175) is dimensioned to abut a gas turbine engine component (64). The main body (72; 172) includes at least one removal feature (78; 178) dimensioned to sever in response to engagement with a cutting tool (TT). A method of assembly is also disclosed.

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A ceramic matrix composite component (100) includes a ceramic matrix composite wall; a coating (107) disposed on the wall; and a cooling hole (102) formed in the wall. The cooling hole (102) has a metering section (104) defined along a first axis (C1) and a diffuser section (106) defined along a second axis (C2) that is offset from the first axis (C1). The cooling hole (102) has a total length (L) defined along the first axis (C1), the total length (L) being the sum of a length of the metering portion (104) and a length of the diffuser portion (102). The length of the metering portion (104) is between about 40 percent and about 85 percent of the total length (L). A ceramic matrix composite airfoil (100) and a method of applying a coating (107) to a ceramic matrix composite component (100) are also disclosed.

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A gas turbine engine (20) includes a first component (62), a second component (64), an anti-rotation tab (80), and a liner (82). The first component (62) has a first wall (66) that includes a first slot (72), and the second component (64) has a second wall (68) that includes a second slot (74) that is in register with the first slot (72) to define a groove (76). The anti-rotation tab (80) extends into the groove (76) and limits rotation of the first component (62) and the second component (64). The liner (82) lines the groove to limit wear between the anti-rotation tab (80) and the first component (62) and between the anti-rotation tab (80) and the second component (64).

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Zusammenfassung wird geladen …

A gas turbine engine (20) including a core having a compressor section (24) fluidly connected to a combustor (56) via a primary flowpath and a turbine section (28) connected to the combustor (56) via the core flow path (C). An assembly is disposed within the gas turbine engine (20) and includes a first part (110) connected to a second part (120) via a radial stack joint. The first part (110) includes a radially inward facing surface (112) contacting a corresponding radially outward facing surface (126) of the second part (120). A fastener (130) protrudes through the first part (110) and the second part (120) and is configured to maintain the relative positions of the first part (110) and the second part (120). A channel (140) is disposed on at least one of the radially inward facing surfaces (112, 126) and is positioned between the fastener (130) and a circumferential edge of the first part (110). The channel (140) is connected to at least one cooling air source (150).

An assembly is provided for a variable vane arrangement (20) of a turbine engine. A platform (22, 24) extends circumferentially about a centerline (28) and radially relative to the centerline between a first platform side (34, 40) and a second platform side (32, 42). The platform includes a plurality of variable vane receptacles (70) arranged in an annular array about the axial centerline (28), which variable vane receptacles include a first variable vane receptacle (70). The first variable vane receptacle is configured with a recess (76), a bore (80) and a shelf (78). The recess (76) extends longitudinally along a variable vane pivot axis (52) into the platform (22, 24) from the first platform side (34, 40) to the shelf (78). The bore (80) extends longitudinally along the variable vane pivot axis (52) into the platform (22, 24) from the shelf (78). An insert (72) includes a sleeve (86) and a plate (88). The sleeve (86) lines at least a portion of the bore (80). The plate (88) is located within the recess (76) adjacent the shelf (78).

A bearing assembly monitoring system (62) includes a bearing assembly (38) supporting rotation of a rotating member (78). The bearing assembly (38) includes a fixed portion and rotatable portion. A piezoelectric element (66) is mounted to the fixed portion and generates an electric signal in response to a vibration of the fixed portion. A first transceiver (80) is electrically coupled to the piezoelectric element (66) to receive the electrical signal generated by the piezoelectric element (66) and generate a signal indicative of the vibration of the fixed portion. A gas turbine engine bearing monitoring system (62) and a method are also disclosed.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A gas turbine engine (20) includes a ceramic wall (62) for bounding an engine core gas path (C). The ceramic wall has a ceramic wall first side (64a) that faces the engine core gas path and a ceramic wall second side (64b) that faces away from the engine core gas path. There is a metallic wall (72) adjacent the ceramic wall second side. The metallic wall has a metallic wall first side (72a) that faces the ceramic wall and a metallic wall second side (72b) that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel (76) there between. There is a seal (78) on the ceramic wall second side, and the metallic wall has at least one cooling hole (80) adjacent the seal for emitting cooling air to cool the seal.

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A method can comprise dividing a heat exchanger design into a plurality of modules (10), the plurality of modules (10) arranged in a grid, each module in the plurality of modules (10) including: a first fluid conduit (161) defining an inlet (1611), an outlet (1612), and a heat-transfer surface (602), and a first flow direction, and a second fluid conduit (162) defining a second inlet, a second outlet, a second heat-transfer surface, and a second flow direction, the second flow direction different from the first flow direction; and determining a heat-transfer augmenter arrangement (1161) for the first fluid conduit (161) and the second fluid conduit (162) of each module in the plurality of modules (10) based on a stress threshold of the module (16) in the plurality of modules (10).

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Zusammenfassung wird geladen …

An inspection device (305) is disclosed herein. In various embodiments, the inspection system device comprises: a support structure (302) ; a motor (404); a shaft (308) operably coupled to the motor (404), the shaft (308) extending from a first side of the support structure (302) to a second side of the support structure (302), the shaft (308) configured to couple to a bladed rotor; and a scanner (310) moveably coupled to the support structure (302), the scanner (310) configured to generate a three-dimensional model for the bladed rotor.