Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount.

Abstract: A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine.

Abstract: A mid-turbine frame is connected to at least one mount of a gas turbine engine for transferring a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a first load structure, a second load structure, and a plurality of struts. The first load structure combines the first load and the second load into a combined load. The second load structure transfers the combined load to the mount. The struts are connected between the first load structure and the second load structure and transfers the combined load from the first load structure to the second load structure.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load structure and a plurality of struts. The single point load structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load structure to the mount.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protruding from the interior surface. The ring structure is connected to each of the plurality of struts at the interior surface at the dimples. The mount is positioned within each of the dimples and transfers load to the engine casing.

Abstract: An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus.

Abstract: An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: A mid-turbine frame is connected to at least one mount of a gas turbine engine for transferring a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a first load structure, a second load structure, and a plurality of struts. The first load structure combines the first load and the second load into a combined load. The second load structure transfers the combined load to the mount. The struts are connected between the first load structure and the second load structure and transfers the combined load from the first load structure to the second load structure.

Abstract: An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protruding from the interior surface. The ring structure is connected to each of the plurality of struts at the interior surface at the dimples. The mount is positioned within each of the dimples and transfers load to the engine casing.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load structure and a plurality of struts. The single point load structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load structure to the mount.

Abstract: A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14, 16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height R. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54).

Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14, 16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54).

Abstract: A premixing fuel injector for an industrial gas turbine engine includes an axially extending centerbody (58) and a pair of radially offset scrolls (18) bounding a mixing chamber (24). The leading end (28) of each scroll cooperates with the trailing end (34) of the neighboring scroll to define an intake slot (42) for admitting a stream of primary combustion air (44) tangentially into the mixing chamber. Fuel injection passages extend along each intake slot for injecting jets (76a, 76b) of primary fuel into the incoming airstream (44). The injector is operable in a prescribed or normal state, and in a degraded state associated with the presence of undesirable combustion inside the mixing chamber. The fuel injection passages are oriented and positioned so that the fuel jets issuing therefrom are ineffective at sustaining the undesirable combustion for more than a limited interval of time.

Abstract: A tangential air entry fuel nozzle has a longitudinal axis and two cylindrical-arc scrolls with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate has a central opening to permit air and fuel to exit into a combustor, while at the opposite end another endplate blocks the nozzle flow area. The scrolls are secured between these endplates. A centerbody is located between the scrolls coaxial with the axis. The centerbody has a base which includes at least one air supply port extending therethrough, and an internal passageway. The centerbody includes a frustum portion and aerodynamic ramps that prevent flow reversal and flame stabilization between the endplates.

Abstract: A method of reducing the tendency of the combustion flame to stabilize within the mixing zone of a tangential entry nozzle is disclosed which comprises mixing fuel and air in a mixing zone within a fuel nozzle assembly, thereby producing a first fuel/air mixture which is isolated from the combustion products by maintaining sufficiently high axial velocities throughout the mixing zone and using a combination of a second internal passageway within a centerbody (either fueled or unfueled) and the surfaces of the combustor inlet port.

Abstract: A tangential air entry fuel nozzle has a combustor inlet port to permit air and fuel to exit into a combustor. The port includes a convergent surface, a combustor surface, and a cylindrical surface extending therebetween. The convergent surface extends a first distance along the longitudinal axis of the nozzle, the cylindrical surface extends a second distance along the axis, and the second distance is at least 30% of the first distance.