RTX Corporation Patente

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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 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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Gas turbine engines (500, 600, 700, 800, 900) are described. The gas turbine engines (500, 600, 700, 800, 900) include a compressor section, a combustor section, a turbine section, and a nozzle (520, 620, 720, 820, 920), wherein the compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle (520, 620, 720, 820, 920). A waste heat recovery system (502, 602, 702, 802, 902) is operably connected to the gas turbine engine (500, 600, 700, 800, 900), the waste heat recovery system (502, 602, 702, 802, 902) having a working fluid. An auxiliary cooling system (540, 640, 740, 840, 940) is configured to provide cooling to a working fluid of the waste heat recovery system (502, 602, 702, 802, 902).

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A propulsion system (20) for an aircraft includes a fan (22), a core engine (24) configured for generating a gas flow (36) utilized to generate shaft power for driving the fan (22), a nacelle (48) that surrounds the core engine (24) and the fan (22), a condenser (58) where water in the gas flow (36) is condensed into a liquid form, an exhaust duct assembly (52) where the gas flow (36) is directed to the condenser (58), an ejector duct (60) where a portion of a bypass airflow (38) is thermally communicated with the condenser (58) to cool the gas flow (36), and an evaporator assembly (54), that is in thermal communication with the exhaust duct (60), where water recovered by the condenser (58) is heated to generate a steam flow (56) that is subsequently communicated to the core engine (24).

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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).

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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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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.

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).

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