Abstract: A compressor shroud assembly is disclosed comprising a dynamically moveable impeller shroud, a static compressor casing, an air piston mounted between said impeller shroud and said compressor casing, and a clearance control system. The air piston effects axial movement of said impeller shroud responsive to a supply of actuating air. The clearance control system regulates the pressure of actuating air in said air piston and comprises a supply conduit having a supply modulating valve and a discharge conduit having a blowoff check valve. The blowoff check valve is set to open at a predetermined differential pressure between pressure of the air piston and pressure of the supply of actuating air.

Abstract: A gas turbine engine is provided. The gas turbine engine may include a geared architecture, a central body support and a bearing package. The geared architecture may interconnect a spool and a fan rotatable about an axis. The central body support may provide an annular wall for a core flow path and an integral flex support inwardly extending therefrom. The integral flex support may couple the geared architecture to the central body support. The bearing package may include a bearing support removably coupled to the integral flex support.

Abstract: A method of assembling a turbine engine is provided. The method includes providing a heat exchanger having a curvilinear body. The method also includes coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine. The curvilinear body facilitates reducing pressure losses in airflow channeled into the heat exchanger.

Abstract: A regenerator (100) for a thermal cycle engine with external combustion, according to the invention comprises a network of fibers wherein a majority of the fibers at least partially encircles the axis of the regenerator. The fibers were part of a fiber web, which is coiled and sintered thereby obtaining the regenerator.

Abstract: A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber walls. The high-speed cantilever shaft has a longitudinal duct and an array of fine orifices in the wall of the shaft for directing pressurized oil jets that impinge on the shaft bearings with little relative speed to increasing wetting of the bearing components. Oil is supplied to the duct by means of a positive-displacement pump directly driven by the output shaft. The pump output pressure is monitored to signal the end of the start-up sequence when the turbine reaches sufficient speed. The turbo-engine further includes devices for decoupling vibrations between the three systems thereof, including a loosely-mounted removable spline pivotable at both ends for coupling the high-speed shaft to the step-down gearbox.

Abstract: A combined cycle power plant (10) has a gas turbine (11), a heat recovery steam generator (16) which is connected downstream to the gas turbine (11) and delivers steam to a steam turbine (19), an exhaust gas recycling line (28) which returns some of the exhaust gases, which flow from the exhaust of the gas turbine (11) through the heat recovery steam generator (16), to the inlet of the gas turbine (11), and also a CO2 separating plant (25) which separates from the non-returned part of the exhaust gases the CO2 which is contained therein and delivers it to a CO2 outlet. A reduction of the equipment cost or a flexible adaptation of the operation can be achieved by a supplementary firing (17) being associated with the heat recovery steam generator (16), which by combusting a carbonaceous fuel produces additional exhaust gases with CO2 content and transmits them through the heat recovery steam generator (16).

Abstract: A gas turbine engine includes a heat exchanger for heating an airflow. The engine is arranged so that in use the heat exchanger is heated and in turn heats the airflow.

Abstract: A turbine includes a combustion chamber with deflectors generating vortices in a secondary gas flow into the combustion chamber, thereby confining the flame front from penetrating into the cold region of the chamber under variable operating conditions, simplifying cooling of the chamber walls. The turbine further includes devices for decoupling vibrations between the high- and low-speed shafts, including a loosely mounted spline coupling the high-speed shaft to the step-down system and disk dampening means coupling the step-down system to the low-speed output shaft.

Abstract: An automotive turbine regenerator system employs sectored matrix elements which are extruded and then assembled into the larger rotary regenerator. Discontinuous rotation is taught such that the seals are not rubbing seals but rather are clamping seals thus radically reducing the leakage and the wear on seal components.

Abstract: A gas turbine engine (10) comprises a first compressor (16), a combustor (22) and a first turbine (24) arranged in flow series. The first turbine (24) is arranged to drive the first compressor (16). The first compressor (16) has variable inlet guide vanes (38) and the first turbine (24) has variable inlet guide vanes (42). A second compressor (48) is arranged upstream of the first compressor (16). An auxiliary intake (12) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). A valve (54) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). The valve (54) is movable between a first position in which the second compressor (48) supplies air to the first compressor (16) and a second position in which the second compressor (48) does not supply fluid to the second compressor (16) and the auxiliary intake (12) supplies fluid to the first compressor (16).

Abstract: The heat exchanger for exchanging heat between compressed air ejected from the compressor and exhaust gas ejected from the turbine rotor is connected to the exhaust gas outlet side on the back portion of the gas turbine. The heat exchanger has the core having a plurality of heat transfer plates for partitioning the first paths for compressed air and the second paths for exhaust gas inside the casing. On the side of the back portion of the core, the first inlets for compressed air are formed and on the side of the front portion of the core, the outlets for compressed air are formed. Between the core and the casing, the introduction path for introducing compressed air into the first inlets is formed. Exhaust gas flowing into the second paths from a position in front of the core is ejected from the back of the core. No pipe for connecting the gas turbine and heat exchanger is required and miniaturization of the gas turbine apparatus and a reduction in cost can be realized.

Abstract: A recuperator for a gas turbine engine comprises a plurality of cells that are orientated in an annular array and attached to one another at only the radially inner edges thereof. Each cell comprises a high pressure plate having spaced integral ribs thereon defining a plurality of low temperature compressed air passages and a low pressure plate having a plurality of spaced ribs defining a plurality of high temperature exhaust gas passages.