FIELD

The present disclosure relates to gas turbine engines, and, more specifically, to a plumbing apparatus for a gas turbine engine.

BACKGROUND

A gas turbine engine typically includes a fan section, a compressor section, a combustor section, and a turbine section. In general, during operation, air is pressurized in the fan and compressor sections and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases flow through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads.

Gas turbine engines may include various cooling systems that employ heat exchangers. Bypass air may be directed across the heat exchangers as a cooling fluid. The inlet piping of the heat exchanger (i.e., the bypass air exiting the heat exchanger) may partially block and/or adversely heat up an engine bay. The piping may also cause pressure loss that may otherwise be used to drive heat rejection in the heat exchanger.

SUMMARY

A conduit assembly is disclosed herein. The conduit assembly may comprise: a pipe; a plurality of hollow passages disposed through the pipe; and a plurality of flow guides disposed in the pipe, each flow guide in the plurality of flow guides at least partially defining a respective hollow passage in the plurality of hollow passages, wherein: the plurality of hollow passages are configured to receive a first fluid, the pipe is configured to receive a second fluid, and the conduit assembly is configured to transfer heat from the first fluid to the second fluid.

In various embodiments, the pipe may include a curved pipe portion having an inner radius portion and an outer radius portion, the plurality of flow guides disposed between the outer radius portion and the inner radius portion. Each flow guide in the plurality of flow guides may comprise a radially inner wall and a radially outer wall. The radially inner wall and the radially outer wall may at least partially define a respective hollow passage in the plurality of hollow passages. The pipe may be a straight pipe portion. The pipe may include a trip strip on a heat transfer surface. Each flow guide in the plurality of flow guides may be configured to guide the first fluid.

A conduit assembly is disclosed herein. The conduit assembly may comprise: a pipe portion configured to receive a first fluid, the pipe portion including a trip strip on a heat transfer surface; and a plurality of hollow passages disposed through the pipe portion, the plurality of hollow passages configured to receive a second fluid.

In various embodiments, the conduit assembly may further comprise a plurality of flow guides disposed in the pipe portion, each flow guide in the plurality of flow guides configured to guide the first fluid. Each flow guide in the plurality of flow guides may at least partially define a respective hollow passage in the plurality of hollow passages. The pipe portion may be a curved pipe portion having an inner radius portion and an outer radius portion, the plurality of flow guides disposed between the outer radius portion and the inner radius portion. Each flow guide in the plurality of flow guides may comprise a radially inner wall and a radially outer wall. The radially inner wall and the radially outer wall may at least partially define a respective hollow passage in the plurality of hollow passages. The pipe portion may be a straight pipe portion.

A gas turbine engine is disclosed herein. The gas turbine engine may comprise: an outer engine case structure; an inner engine case structure disposed radially inward from the outer engine case structure, the outer engine case structure and the inner engine case structure defining a bypass duct configured to receive an airflow; a conduit assembly at least partially disposed in the bypass duct, the conduit assembly comprise a pipe and a plurality of hollow passages disposed through the pipe, the conduit assembly configured to receive a fluid, the plurality of hollow passages configured to receive the airflow.

In various embodiments, the gas turbine engine may further comprise a heat exchanger in fluid communication with the conduit assembly. The gas turbine engine may further comprise a plurality of flow guides disposed in the pipe, each flow guide in the plurality of flow guides configured to guide the fluid. The pipe may include a curved pipe portion having an inner radius portion and an outer radius portion, the plurality of flow guides disposed between the outer radius portion and the inner radius portion. Each flow guide in the plurality of flow guides may comprises a radially inner wall and a radially outer wall. The radially inner wall and the radially outer wall may at least partially define a respective hollow passage in the plurality of hollow passages.

The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be exemplary in nature and non-limiting.

