A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.

A turbine section for a gas turbine engine includes an independently controllable wheel downstream of the first static vane structure and a turbine rotor downstream of the independently controllable wheel. A method of generating thrust for a gas turbine engine, includes rotating a independently controllable wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.

A double-flow type volute casing having a structure for changing the direction of flow in a turbine inlet is proposed. The volute casing includes a partition plate for partitioning a volute defined in the casing into an inner flow channel and an outer flow channel, provided so as to surround a turbine, a plurality of flow-rate adjustment holes formed in the partition plate so as to be arranged at a gradually decreasing interval such that a high-pressure fluid flowing in the outer flow channel is introduced into the inner flow channel and the fluid flowing in the inner flow channel is directed perpendicularly to the turbine blades, in order to minimize the amount of energy that is lost and to reduce imbalanced variation of torque applied to the turbine blades.

A double-flow type volute casing having a structure for changing the direction of flow in a turbine inlet is proposed. The volute casing includes a partition plate for partitioning a volute defined in the casing into an inner flow channel and an outer flow channel, provided so as to surround a turbine, a plurality of flow-rate adjustment holes formed in the partition plate so as to be arranged at a gradually decreasing interval such that a high-pressure fluid flowing in the outer flow channel is introduced into the inner flow channel and the fluid flowing in the inner flow channel is directed perpendicularly to the turbine blades, in order to minimize the amount of energy that is lost and to reduce imbalanced variation of torque applied to the turbine blades.

A method of operating a compressor of a gas turbine engine is described which includes directing a main airflow through tandem stator rows in a gaspath of the compressor, extracting a first portion of the main airflow from a first location proximate radially inner roots of stators of the first or second stator rows, extracting a second portion of the main airflow from a second location proximate the radially inner roots of the stators of the first or second stator rows, the second location being downstream of the first location relative to the main airflow, and re-injecting the combined extracted flow back into the main airflow at a third location. The third location is located upstream of the first and second locations, and is upstream of a leading edge of stators of the first stator row.

A method of operating a compressor of a gas turbine engine is described which includes directing a main airflow through tandem stator rows in a gaspath of the compressor, extracting a first portion of the main airflow from a first location proximate radially inner roots of stators of the first or second stator rows, extracting a second portion of the main airflow from a second location proximate the radially inner roots of the stators of the first or second stator rows, the second location being downstream of the first location relative to the main airflow, and re-injecting the combined extracted flow back into the main airflow at a third location. The third location is located upstream of the first and second locations, and is upstream of a leading edge of stators of the first stator row.

A micro gas turbine equipped with a valve mechanism by means of which the operation of the micro gas turbine can be influenced and optimized, particularly by regulating a supply of hot gas from the cabinet and/or the exhaust of the micro gas turbine to an inlet side of the compressor. When the temperature of ambient air is relatively low, thermal output and thermal efficiency of a micro gas turbine decrease. The present micro gas turbine compensates for the loss of thermal efficiency.

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.

A method of operating a compressor of a gas turbine engine is described which includes directing a main airflow through tandem stator rows in a gaspath of the compressor, extracting a first portion of the main airflow from a first location proximate radially inner roots of stators of the first or second stator rows, extracting a second portion of the main airflow from a second location proximate the radially inner roots of the stators of the first or second stator rows, the second location being downstream of the first location relative to the main airflow, and re-injecting the combined extracted flow back into the main airflow at a third location. The third location is located upstream of the first and second locations, and is upstream of a leading edge of stators of the first stator row.