In an exemplary embodiment, a method for manufacturing turbine wheel airfoils includes: defining an initial design with an initial respective line for a straight line cut for a respective surface of each airfoil; evaluating an initial score for the initial design based on mechanical, aerodynamic, manufacturing cost, and robustness criteria; performing, in an iterative manner, a sequence of changes to the initial design, by adjusting the initial respective line for the straight line cut for the respective surface of each airfoil to generate different iterative designs; evaluating respective scores for each of the different iterative designs; selecting a design from the initial design and the different iterative designs that generates an optimized score based on the mechanical, aerodynamic, manufacturing cost, and robustness criteria; and cutting along the straight line for the surface of each airfoil, based on the selected design, to form each airfoil.

A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

A fan frame includes a first frame and a second frame. The first frame includes at least a first sidewall and a first connecting element, wherein the first connecting element is disposed on the first sidewall. The second frame includes at least a second sidewall and a second connecting element, wherein the second connecting element is disposed on the second sidewall and at least partially overlapped with the first connecting element. The second connecting element includes a first end and a second end in a first direction, wherein the first end and the second end are bent toward the first connecting element, respectively, for grasping the first connecting element. As a result, the accuracy error and the precision error are avoided, the stresses are internally counterbalanced, and the deformation of the fan frame is avoided.

An additively manufactured impingement structure for a component is provided. The control structure includes an outer wall, an inner wall, and an impingement wall positioned between the outer wall and the inner wall. A fluid distribution passageway is defined between the inner wall and the impingement wall and an impingement gap is defined between the impingement wall and the outer wall. A plurality of impingement holes are defined in the impingement wall to provide fluid communication between the fluid distribution passageway and the impingement gap. A flow of cooling or heating fluid may be supplied to the fluid distribution passageway which distributes the flow and impinges it through the impingement holes onto the outer wall to cool or heat the outer wall, respectively.

A sump housing apparatus for a gas turbine engine includes: an annular body; and a plurality of service tubes arrayed around the body, each service tube having a proximal end intersecting the body and an opposed distal end, each service tube having an inner port communicating with an interior of the body; wherein the body and at least one of the service tubes are part of a monolithic whole.

A cooling device for an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.