A multiple number of rotatable, axial flow turbine blades having a common platform and shroud portion from which two arcuately separated, axially extending, side entry roots protrude radially inwardly toward the axis of rotation of a rotatable shaft.

Multiple side entry root for multiple blade group

Power management fuel control for plural gas turbine engines

A ceramic blade for a hybrid type gas turbine blade has a dovetail portion, a platform portion formed on the dovetail portion and blade portions formed on the platform portion. The number of the blade portions formed on one platform portion is two or more. The upper surface of the platform portion is shaped into an arc-like form, and the dovetail portion is linearly formed in a tangential direction to a turbine rotation direction. By the utilization of this blade, the hybrid type gas turbine blade can inhibit the leakage of a gas and can be easily manufactured and is excellent in durability.

Blade, turbine disc and hybrid type gas turbine blade

In one aspect a propulsion system comprises an engine and a drive assembly coupled to the engine, comprising a first driveshaft rotatable in a first direction about a first axis, a first fan coupled to the first driveshaft to rotate in the first direction, and a clutch assembly to selectively disengage the first fan from the first driveshaft. Other aspects may be described.

Contra-rotating open fan propulsion system

A rotor blade pair for rotation around an axial centerline is provided which includes a platform, a first and a second airfoil, and a root having a first and second wall. The platform has an inner and an outer radial surface. The first and second airfoils extend out from the outer radial surface of the platform. The root walls extend out from said inner radial surface of the platform, and are integrally connected to one another, forming a hollow between the walls and the inner radial surface. The first wall is substantially aligned with the first airfoil and the second wall is substantially aligned with the second airfoil.

Turbine engine rotor blade pair

The invention concerns a gas turbine engine axial flow multistage compressor having a rotor member, and a plurality of platform elements each of which has rotor blade members mounted thereon and each of which is itself disposed radially outwardly of and spaced from the rotor member, the plurality of platform elements defining an annular platform member and the axially consecutive annular platform member of different stages of rotor blade members contacting each other to form a drumlike structure.

Gas turbine engine axial flow multistage compressor

Fluid coupling and friction clutches

Power output fuel control means for plural engines

Rotor member for a rotary wing aircraft

885,272. Clutches. ROLLS-ROYCE Ltd. Feb. 12, 1960 [Feb. 23, 1959], No. 6242/59. Class 80 (2). In order to prevent wear and overheating of a friction clutch due to residual friction when disengaged, a synchronized dog clutch is interposed between the friction clutch and a driving shaft and is disengaged upon disengagement of the friction clutch. The friction clutch does not engage until the dog clutch has engaged. A driving shaft 26 is axially slidable and has internal dog teeth 27 engageable with dog teeth 28 provided on an end plate 28 1 of a casing 29 of the friction clutch which has plates 31, 33 splined to the casing and a driven shaft 24. Synchronizing means for the dog clutch comprises a sleeve 78 axially slidable on a flange 79 formed on an enlarged portion 26 1 of the driving shaft 26, the sleeve 78 having helical serrations 81 engaging serrations 82 on the enlarged portion 26 1 and a surface 86 on the sleeve being frictionally engageable with the end plate 28 1 . In operation, low-pressure liquid is permanently supplied to a clearance 53 between coaxial tubes 51, 52, and to engage the clutch high-pressure liquid is supplied to the interior of the tube 52 whence it passes through ports 74, 73, 72 to a chamber 71 to act on a plate 69 fast with the input shaft 26 to move it towards the right. Liquid from chamber 71 leaks through a clearance between sleeves 70, 41 and enters a chamber 85 whence it is centrifuged through ports 84 into a chamber 83 to shift the sleeve 78 to the right to engage the surfaces 86, 87. This effects rotation of the casing 29 and facilitates engagement of the dog teeth 27, 28 which occurs immediately thereafter. Movement of the plate 69 to the right uncovers ports 75 so that high-pressure oil is admitted to a chamber 76 and thence through ports 45 to a chamber 77 to act on a piston 38 a skirt 36 of which acts on a presser member 35 so that the friction clutch engages. To disengage the drive, the interior of tube 52 is opened to exhaust. Low-pressure liquid continues to be supplied through the clearance 53 and through ports 55, 54 to a chamber 56 to retract the piston 38 and so disengages the friction clutch. Low-pressure liquid is also supplied through a passage 68 to a chamber 67 to retract the shaft 26 thus disengaging the dog clutch. Specification 885,271 is referred to.

Bracey Kenneth Edward George

Papers

Gas turbine engine axial flow multistage compressor

Fluid coupling and friction clutches

Power output fuel control means for plural engines

Rotor member for a rotary wing aircraft

Improvements in or relating to clutch mechanisms