Abstract: A gas turbine engine comprising: an inner core nacelle; an outer fan nacelle; a bypass duct between the inner core nacelle and the outer fan nacelle; at least one bifurcation that extends between the inner core nacelle and the outer fan nacelle; and a cooling system, wherein the cooling system comprises at least one pipe for conveying a fluid to be cooled, the at least one pipe forming part of a fluid system of the engine, wherein the at least one pipe passes through the at least one bifurcation, and wherein at least a portion of one or more of the pipes is arranged to bring the fluid to be cooled into a heat exchanging relationship with a fluid, e.g. air, flowing in the bypass duct.

Abstract: A gas turbine engine comprising: an inner core nacelle; an outer fan nacelle; a bypass duct between the inner core nacelle and the outer fan nacelle; at least one bifurcation that extends between the inner core nacelle and the outer fan nacelle; and a cooling system, wherein the cooling system comprises at least one pipe for conveying a fluid to be cooled, the at least one pipe forming part of a fluid system of the engine, wherein the at least one pipe passes through the at least one bifurcation, and wherein at least a portion of one or more of the pipes is arranged to bring the fluid to be cooled into a heat exchanging relationship with a fluid, e.g. air, flowing in the bypass duct.

Abstract: Apparatus for a gas turbine engine, the apparatus comprising: an engine core; a nacelle; and thermal energy transfer apparatus configured to transfer thermal energy from the engine core to the nacelle.

Abstract: A gas turbine engine comprising a turbine section cooling system and a method of cooling a turbine section of a gas turbine engine is provided. The gas turbine engine comprises in flow series a compressor section, a combustor, and a turbine section, the engine further comprising a turbine section cooling system. The turbine section cooling system including a first compressed air bleed arrangement and a second compressed air bleed arrangement. The first compressed air bleed arrangement bleeds a first flow of compressed air from a high pressure stage of the compressor section. The first flow of compressed air bypasses the combustor and arrives at the turbine section to form a sealing and/or cooling flow at a row of stator vanes upstream of an adjacent rotor disc. The second compressed air bleed arrangement bleeds a second flow of compressed air from one or more lower pressure stages of the compressor section.

Abstract: A gas turbine engine comprising a turbine section cooling system and a method of cooling a turbine section of a gas turbine engine is provided. The gas turbine engine comprises in flow series a compressor section, a combustor, and a turbine section, the engine further comprising a turbine section cooling system. The turbine section cooling system including a first compressed air bleed arrangement and a second compressed air bleed arrangement. The first compressed air bleed arrangement bleeds a first flow of compressed air from a high pressure stage of the compressor section. The first flow of compressed air bypasses the combustor and arrives at the turbine section to form a sealing and/or cooling flow at a row of stator vanes upstream of an adjacent rotor disc. The second compressed air bleed arrangement bleeds a second flow of compressed air from one or more lower pressure stages of the compressor section.

Abstract: A control mechanism for moving at least two components of a gas turbine engine, the control mechanism comprises first and second crankshafts and a torsion bar connected to both crankshafts, each crankshaft is connected to a different component, the crankshafts engage one another via one-way abutment means and the torsion bar is pre-twisted so that up to a predetermined rotational extent the two crankshafts rotate together and beyond that extent only the first crankshaft rotates, thereby one of the two components moves more than the other component.

Abstract: A load absorption arrangement 40 for absorbing loads in a variable stator vane positioning system of a gas turbine engine includes a valve 42 which has a first operating condition to enable the load absorption arrangement 40 to transmit load, and a second operating condition, which is operable above a predetermined load, in which the valve 42 can release to enable the load absorption arrangement 40 to absorb the load thereon. The arrangement 40 is particularly suitable for absorbing shock loads which may arise under engine surge.

Abstract: A control mechanism for moving at least two components of a gas turbine engine, the control mechanism comprises first and second crankshafts and a torsion bar connected to both crankshafts, each crankshaft is connected to a different component, the crankshafts engage one another via one-way abutment means and the torsion bar is pre-twisted so that up to a predetermined rotational extent the two crankshafts rotate together and beyond that extent only the first crankshaft rotates, thereby one of the two components moves more than the other component.