Abstract: A heat shield may include a base portion, wherein the base portion bounds a triangular void, a top portion, wherein the top portion bounds an ovular void, and a tapered portion, wherein the tapered portion extends between the base portion and the top portion, the top portion having a smaller cross-sectional area than the base portion.

Abstract: A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. The sidewall portion may extend at an angle between 80 degrees and 100 degrees from the top portion. The sidewall portion may bound a hexagonal void. The flexible tab may comprise an angle between 80 degrees and 100 degrees. The flexible tab may be fixed to the sidewall portion, wherein the flexible tab is configured to be attached to a fitting.

Abstract: A heat shield comprising a base portion, a top portion, and a tapered portion extending between the top portion and the bottom portion is described herein, in accordance with various embodiments. The base portion may comprise a sheet metal bounding a triangular void. The top portion may comprise a sheet metal bounding an ovular void.

Abstract: A heat shield may include a base portion, wherein the base portion bounds a triangular void, a top portion, wherein the top portion bounds an ovular void, and a tapered portion, wherein the tapered portion extends between the base portion and the top portion, the top portion having a smaller cross-sectional area than the base portion.

Abstract: A fitting is configured to couple a portion of a frame of a turbine and a bearing housing on an aircraft engine. The fitting includes a first receptacle configured to seat a tube that is configured to convey oil or air, and at least a second receptacle configured to seat a corresponding at least two bolts associated with the bearing housing, wherein the fitting comprises sections between the first receptacle and the at least a second receptacle that have a material thickness in a range of 3.175 millimeters and 6.35 millimeters.

Abstract: A fitting for attaching to double wall tubes includes a body, a fitting center port, an outer seal, a tube connection, a pad connection, an inner seal, a groove, and a diagnostic port. The body has a first surface on a first side of the body and a second surface on a second side of the body. The fitting center port extends through the body for passing a primary fluid flow. The tube connection is on the first side of the fitting, and includes an inner connection and an outer connection. The groove is in the second surface surrounding the inner seal and the groove is configured to receive an outer seal. The diagnostic port is in the second surface for transferring a collected fluid through the body to the outer connection.

Abstract: A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. The sidewall portion may extend at an angle between 80 degrees and 100 degrees from the top portion. The sidewall portion may bound a hexagonal void. The flexible tab may comprise an angle between 80 degrees and 100 degrees. The flexible tab may be fixed to the sidewall portion, wherein the flexible tab is configured to be attached to a fitting.

Abstract: A coupling arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a conduit between a first frame case defining a frame axis and a second frame case. A flange is coupled to the conduit defining a first axis and abuts the first frame case. A capture plate coupled to the conduit defines a second axis and abuts the second frame case. The first axis is offset relative to the second axis in an axial direction relative to the frame axis.

Abstract: A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. The sidewall portion may extend at an angle between 80 degrees and 100 degrees from the top portion. The sidewall portion may bound a hexagonal void. The flexible tab may comprise an angle between 80 degrees and 100 degrees. The flexible tab may be fixed to the sidewall portion, wherein the flexible tab is configured to be attached to a fitting.

Abstract: A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. The sidewall portion may extend at an angle between 80 degrees and 100 degrees from the top portion. The sidewall portion may bound a hexagonal void. The flexible tab may comprise an angle between 80 degrees and 100 degrees. The flexible tab may be fixed to the sidewall portion, wherein the flexible tab is configured to be attached to a fitting.

Abstract: A coupling arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a conduit between a first frame case defining a frame axis and a second frame case. A flange is coupled to the conduit defining a first axis and abuts the first frame case. A capture plate coupled to the conduit defines a second axis and abuts the second frame case. The first axis is offset relative to the second axis in an axial direction relative to the frame axis.

Abstract: A heat shield comprising a base portion, a top portion, and a tapered portion extending between the top portion and the bottom portion is described herein, in accordance with various embodiments. The base portion may comprise a sheet metal bounding a triangular void. The top portion may comprise a sheet metal bounding an ovular void.

Abstract: A fitting for attaching to double wall tubes includes a body, a fitting center port, an outer seal, a tube connection, a pad connection, an inner seal, a groove, and a diagnostic port. The body has a first surface on a first side of the body and a second surface on a second side of the body. The fitting center port extends through the body for passing a primary fluid flow. The tube connection is on the first side of the fitting, and includes an inner connection and an outer connection. The groove is in the second surface surrounding the inner seal and the groove is configured to receive an outer seal. The diagnostic port is in the second surface for transferring a collected fluid through the body to the outer connection.

Abstract: Aspects of the disclosure are directed to installing a test assembly on an aircraft engine, connecting a vacuum source to at least one port of the test assembly, engaging the vacuum source, and based on determining that a vacuum is maintained in an amount greater than a threshold, determining that a plurality of seals are present in the engine.

Abstract: Aspects of the disclosure are directed to a fitting configured to couple a portion of a frame of a turbine and a bearing housing on an aircraft engine, comprising: a first receptacle configured to seat a tube that is configured to convey oil or air, and at least a second receptacle configured to seat a corresponding at least two bolts associated with the bearing housing, wherein the fitting comprises sections between the first receptacle and the at least a second receptacle that have a material thickness in a range of 3.175 millimeters and 6.35 millimeters.

Abstract: The present disclosure relates generally to the field of tubes for carrying fluids. More specifically, the present disclosure relates to a tube having an oval shaped cross-section. In some embodiments, the tube with oval cross-section comprises a tube within a cavity in a gas turbine engine.