Gas turbine engines and bladed rotors therefor

Claim 2

A bladed rotor, suitable for a gas turbine engine of the bypass type, including a hub, which carries, so as to be rotatable therewith, at least one pump operable upon rotation of the rotor, a liquid-pressure-operable actuator for adjusting the blades of the rotor to vary flow of fluid over the blades, control valve means by way of which liquid under preSsure is directed from said pump to operate the actuator, and a further pump operable, when said one pump is inoperative or substantially so, by motor means carried by non-rotative structure external of the rotor to supply pressure liquid to the actuator for feathering of the blades.

Claim 3

A gas turbine engine of the by-pass type comprising a compressor, a combustion section, a turbine section, a by-passs duct and a rotor, rotatable in said duct, which has a hub and adjustable blades carried by the hub, wherein said hub includes, disposed wholly therein so as to be rotatable all as one therewith, (a) a liquid reservoir, (b) at least one pump operable upon rotation of the rotor to draw liquid only from said reservoir, (c) a liquid-pressure-operable actuator connected to said blades for effecting adjustment thereof, and (d) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, input means extending from non-rotative structure external of the rotor to the interior of said hub for transmitting input signals to said control valve means for initiating adjustment of the actuator and thus of the blades.

Claim 4

A gas turbine engine of the by-pass type comprising a compressor, a combustion section, a turbine section, a by-passs duct and a rotor, rotatable in said duct, which has a hub and adjustable blades carried by the hub, wherein said hub includes, disposed wholly therein so as to be rotatable all as one therewith, (a) a liquid reservoir, (b) at least one pump operable upon rotation of the rotor to draw liquid only from said reservoir, (c) a liquid-pressure-operable actuator connected to said blades for effecting adjustment thereof, and (d) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, input means extending from non-rotative structure external of the rotor to the interior of said hub for transmitting input signals to said control valve means for initiating adjustment of the actuator and thus of the blades.

Claim 5

A gas turbine engine of the by-pass type comprising a compressor, a combustion section, a turbine section, a by-pass duct and a rotor, rotatable in said duct, which has a hub and adjustable blades carried by the hub, wherein an annular baffle which at least in part defines a liquid reservoir of annular form is housed wholly within the hub, said baffle being fast with the hub so as to be rotatable as one therewith, and said hub further including, disposed wholly therein so as to be rotatable all as one therewith, (a) at least one pump operable upon rotation of the rotor to draw liquid only from said reservior, (b) a liquid-pressure-operable actuator connected to said blades for effecting adjustment thereof, and (c) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, input means extending from non-rotative structure external of the rotor to the interior of said hub for transmitting input signals to said control valve means for initiating adjustment of the actuator and thus of the blades.

Claim 6

A gas turbine engine of the by-pass type comprising a compressor, a combustion section, a turbine section, a by-pass duct and a rotor, rotatable in said duct, which has a hub and adjustable blades carried by the hub, wherein an annular baffle which at least in part defines a liquid reservoir of annular form is housed wholly within the hub, said baffle being fast with the hub so as to be rotatable as one therewith, and said hub further including, disposed wholly therein so as to be rotatable all as one therewith, (a) at least one pump operable upon rotation of the rotor to draw liquid only from said reservior, (b) a liquid-pressure-operable actuator connected to said blades for effecting adjustment thereof, and (c) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, input means extending from non-rotative structure external of the rotor to the interior of said hub for transmitting input signals to said control valve means for initiating adjustment of the actuator and thus of the blades.

Claim 7

An engine as claimed in claim 3, wherein upon rotation of the rotor said pump is operable by means of shafting, an end portion of which is held fast with respect to non-rotative engine structure.

Claim 8

An engine as claimed in claim 3, wherein the actuator is of vane-type and has its axis of rotation coincident with the axis of rotation of the rotor.

Claim 9

An engine as claimed in claim 4, wherein said rotor carries a further pump, which, when said one pump is inoperative or substantially so, is operable by motor means carried by non-rotative engine structure to supply pressure liquid to the actuator for feathering of the blades.

Claim 10

An engine as claimed in claim 6, wherein said reservoir comprises two parts, one associated with said one pump and the other associated with said further pump.

Claim 11

An engine as claimed in claim 6, wherein further shafting is provided whereby said further pump is operable upon rotation of the rotor, an end portion of said further shafting having means associated therewith for holding it fast with respect to non-rotative engine structure, and said associated means being released when the motor means is required to operate said further pump.

Claim 12

A bladed rotor, suitable for a gas turbine engine of the by-pass type, including a hub and adjustable blades carried by the hub, said hub including, disposed wholly therein so as to be rotatable all as one therewith, (a) a liquid reservoir, (b) at least one pump operable upon rotation of the rotor to draw liquid only from said reservoir, (c) a liquid-pressure-operable actuator connected to said blades for effecting adustment thereof, (d) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, and (e) a further pump which is Operable, when said one pump is inoperative or substantially so, by motor means carried by non-rotative structure external of the rotor to supply pressure liquid to the actuator for feathering of said blades.

Claim 13

A bladed rotor, suitable for a gas turbine engine of the by-pass type, including a hub and adjustable blades carried by the hub, said hub including, disposed wholly therein so as to be rotatable all as one therewith, (a) a liquid reservoir, (b) at least one pump operable upon rotation of the rotor to draw liquid only from said reservoir, (c) a liquid-pressure-operable actuator connected to said blades for effecting adustment thereof, (d) control valve means by way of which liquid discharged under pressure by said pump is directed to operate said actuator, and (e) a further pump which is Operable, when said one pump is inoperative or substantially so, by motor means carried by non-rotative structure external of the rotor to supply pressure liquid to the actuator for feathering of said blades.