Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.

Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.

Abstract: A method is provided of determining the internal cross-sectional area of a pipe along its length. The method includes the steps of: (a) filling the pipe with a first fluid; (b) feeding a second fluid into the pipe at a known flow rate, a meniscus being formed between the first and the second fluid, and the meniscus moving along the pipe as the second fluid displaces the first fluid in the pipe; (c) ultrasonically detecting the position of the meniscus as it moves along the pipe; and (d) determining from the second fluid flow rate and the meniscus position, the internal cross-sectional area of the pipe along its length.

Abstract: A method for inspecting the interior of a non-horizontal pipe includes (a) filling the pipe with a first fluid, (b) feeding a second fluid into a lower part of the pipe when the second fluid is more dense than the first fluid or into an upper part of the pipe when the second fluid is less dense than the second fluid the pipe, a meniscus forming between the first and the second fluid and moving along the pipe, (c) introducing an inspection device having an average density between the densities of the first and second fluids such that the device locates at and moves with the meniscus, (d) obtaining inspection data from the inspection device as the device moves along the pipe, (e) determining positions of the meniscus as it moves along the pipe, and (f) relating the meniscus positions to positions at which the inspection data is obtained.

Abstract: A heat exchanger is provided in which heat exchanger shells are formed by electro forming about a mandrel. The shells are attached and joined to provide a heat exchanger module. As the shells are not press formed problems with respect to material elongation to achieve deep grooves in the shells are potentially avoided and shells can be created with more desirable thickness to achieve more efficient heat exchange. Furthermore, reduced shell thickness will also reduce weight and therefore improve the acceptability of heat exchangers in particular applications such as those associated with aerospace and automotive sports.

Abstract: Blade arrangements formed in a blisk configuration include a number of blades secured integrally or through welds or similar bonding to a rotor disc. The blades may be subject to vibration and it would be desirable to provide heat protection to junctions between the blades and the rotor. By providing insert elements between adjacent platform sections of a blade pair, vibrational damping as well as heat shielding and capability with regard to aerodynamic profiling is achieved.

Abstract: A method for inspecting the interior of a non-horizontal pipe includes (a) filling the pipe with a first fluid, (b) feeding a second fluid into a lower part of the pipe when the second fluid is more dense than the first fluid or into an upper part of the pipe when the second fluid is less dense than the second fluid the pipe, a meniscus forming between the first and the second fluid and moving along the pipe, (c) introducing an inspection device having an average density between the densities of the first and second fluids such that the device locates at and moves with the meniscus, (d) obtaining inspection data from the inspection device as the device moves along the pipe, (e) determining positions of the meniscus as it moves along the pipe, and (f) relating the meniscus positions to positions at which the inspection data is obtained.

Abstract: A method is provided of determining the internal cross-sectional area of a pipe along its length. The method includes the steps of: (a) filling the pipe with a first fluid; (b) feeding a second fluid into the pipe at a known flow rate, a meniscus being formed between the first and the second fluid, and the meniscus moving along the pipe as the second fluid displaces the first fluid in the pipe; (c) ultrasonically detecting the position of the meniscus as it moves along the pipe; and (d) determining from the second fluid flow rate and the meniscus position, the internal cross-sectional area of the pipe along its length.

Abstract: A ceramic seal segment for a shroud ring of a rotor of a gas turbine engine, the ceramic seal segment positioned radially adjacent the rotor and characterized by being a hollow section that defines an inlet and an outlet for the passage of coolant therethrough.

Abstract: Sensors (32, 52, 72) for determining a gap between a conductive member (34, 54, 74) such as a blade in a gas turbine engine and a seal segment (31, 51) are known to use capacitive variants in order to create an electrical signal indicative of the gap width. Thermal disparities can create problems with regard to sensor aging and accuracy. By creating a sensor incorporating a metal rod (33, 53, 74) typically integrally formed or associated with the seal segment (31, 51) and coupled through inductive coupling loops (35, 36; 55, 56; 75) it is possible to create a tuned circuit with a Q value which is more stable and therefore acceptable with regard to producing more accurate results at elevated temperatures with less problems with regard to thermal disparities.

Abstract: Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding.

Abstract: Blade arrangements 130 may be formed in a blisk configuration comprising a number of blades secured integrally or through welds or similar bonding to a rotor disc. The blades may be subject to vibration and it would be desirable to provide heat protection to junctions 33 between the blades and the rotor 31. By providing insert elements 34 between adjacent platform sections 35 of a blade pair vibrational damping as well as heat shielding and capability with regard to aerodynamic profiling is achieved.

Abstract: A pressure rise combustor is provided with fuel provided at intermittent periods. The fuel is pulsed at timings such that the phase lag between the addition of the fuel and a resultant pressure rise is minimized. The fuel is pulsed such that the unsteady addition of heat reinforces the amplitude of an unsteady pressure fluctuation.

Abstract: Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding.

Abstract: A pressure rise combustor is provided with fuel provided at intermittent periods. The fuel is pulsed at timings such that the phase lag between the addition of the fuel and a resultant pressure rise is minimised. The fuel is pulsed such that the unsteady addition of heat reinforces the amplitude of an unsteady pressure fluctuation.

Abstract: A heat exchanger is provided in which heat exchanger shells are formed by electro forming about a mandrel. The shells are attached and joined to provide a heat exchanger module. As the shells are not press formed problems with respect to material elongation to achieve deep grooves in the shells are potentially avoided and shells can be created with more desirable thickness to achieve more efficient heat exchange. Furthermore, reduced shell thickness will also reduce weight and therefore improve the acceptability of heat exchangers in particular applications such as those associated with aerospace and automotive sports.

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).

Abstract: Sensors (32, 52, 72) for determining a gap between a conductive member (34, 54, 74) such as a blade in a gas turbine engine and a seal segment (31, 51) are known to use capacitive variants in order to create an electrical signal indicative of the gap width. Thermal disparities can create problems with regard to sensor ageing and accuracy. By creating a sensor incorporating a metal rod (33, 53, 74) typically integrally formed or associated with the seal segment (31, 51) and coupled through inductive coupling loops (35, 36; 55, 56; 75) it is possible to create a tuned circuit with a Q value which is more stable and therefore acceptable with regard to producing more accurate results at elevated temperatures with less problems with regard to thermal disparities.

Abstract: A ceramic seal segment for a shroud ring of a rotor of a gas turbine engine, the ceramic seal segment positioned radially adjacent the rotor and characterized by being a hollow section that defines an inlet and an outlet for the passage of coolant therethrough.