Abstract: A fastener assembly may be configured to mount structures in a gas turbine engine. The fastener assembly may comprise a fastener and a leak resistant insert. The leak resistant insert may be configured to at least partially reduce fluid leakage between the coupling of the fastener and the leak resistant insert. The leak resistant insert may comprise an outer surface opposite an inner threaded surface. The inner threaded surface may define an insert opening through leak resistant fastener insert, configured to receive the fastener. The outer surface may define an insert end enclosing the inner threaded surface opposite the insert opening.

Abstract: A fastener assembly may be configured to mount structures in a gas turbine engine. The fastener assembly may comprise a fastener and a leak resistant insert. The leak resistant insert may be configured to at least partially reduce fluid leakage between the coupling of the fastener and the leak resistant insert. The leak resistant insert may comprise an outer surface opposite an inner threaded surface. The inner threaded surface may define an insert opening through leak resistant fastener insert, configured to receive the fastener. The outer surface may define an insert end enclosing the inner threaded surface opposite the insert opening.

Abstract: A pair of reactant cover plates, e.g., fluid manifolds or protective covers (11, 12), on opposite sides of a fuel cell stack (7) are drawn to the fuel cells (14) and pressure plates (8) by tensioning lines, e.g., cables (23) or straps (23a), which may extend around structures, e.g., pins or extensions (11a, 12a; 11e, 12e) extending outwardly from the ends of the cover plates or guides (22a) on the stack, e.g., on the pressure plates in a closed loop, and are tensioned by a tensioning device, such as a turnbuckle (24).

Abstract: A pair of reactant cover plates, e.g., fluid manifolds or protective covers (11, 12), on opposite sides of a fuel cell stack (7) are drawn to the fuel cells (14) and pressure plates (8) by tensioning lines, e.g., cables (23) or straps (23a), which may extend around structures, e.g., pins or extensions (11a, 12a; 11e, 12e) extending outwardly from the ends of the cover plates or guides (22a) on the stack, e.g., on the pressure plates in a closed loop, and are tensioned by a tensioning device, such as a turnbuckle (24).

Abstract: A power plant (10) having a pair of substantially identical fuel cell stacks (12, 13), each having an oxidant or fuel inlet/outlet manifold (15, 16) identical to the inlet/outlet manifold of the other stack, each inlet/outlet manifold mounted on the same side of the corresponding stack as the other inlet/outlet manifold on the other stack (the right side herein). Inlet/outlet plumbing is disposed at the end of one of the stacks (12) between the inlet/outlet manifolds (15, 16), the plumbing including a T-like transition (43) between a supply pipe (46) and an inlet tube (39) that feeds the inlets of both of the inlet/outlet manifolds (15, 16). At each inlet/outlet manifold, the side which is not connected to plumbing is blocked off with a seal plate (25, 32). Inlet and outlet tubes (38, 39) include flexible tubing portions, whereby to allow for dimensional and/or positional variations between fuel cell power plants.

Abstract: A pair of reactant gas manifolds (11 and 12) on opposite sides of a fuel cell stack (7) are sealed to the fuel cells (14) and pressure plates (8) by means of pressure applied by load cables (17). The centers of the manifolds are prevented from having leakage between them and the end plates by means of a tensioning system comprising a plurality of pins (22) extending outwardly from the ends of the manifolds, and tensioning cables (23) extending around the pins in a closed loop and tensioned by a turnbuckle (24).

Abstract: A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the downstream flap along a forward portion thereof for actuating the upstream flaps and downstream flaps between a number of throat area conditions while permitting mode changes.

Abstract: The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on a torque shaft that rotates to move a connecting link attached to the convergent flap of the nozzle. A pressure balancing hood is attached to the top surface on the forward end of the convergent flap to augment the lowering of the horsepower requirements. In another embodiment a tie rod/end cup arrangement and two piece torque shaft are utilized for ease of removal of the actuation system from the exhaust nozzle assembly.