Gas turbine engine with entrained particle separation system and method

1 . A gas turbine engine, comprising:

a fan section;

a compressor section that includes a compressor inlet disposed downstream of the fan section;

a combustion section;

a turbine section;

a core gas path that begins at the compressor inlet and extends through the compressor section, the combustion section, and the turbine section;

a bypass air path that is disposed downstream of the fan section and radially outside of the core gas path;

a structural member that extends radially across the bypass air path; and

an entrained debris removal system that includes an inlet port engaged with the core gas path, a passage that extends through the structural member, and an exit port that is disposed in contact with ambient air;

wherein the entrained debris removal system is configured to selectively receive core gas from the core gas path and pass the core gas through the passage that extends through the structural member and out of the exit port;

wherein the compressor section includes a low pressure compressor (LPC) section and the inlet port is engaged with the core gas flow path at a position forward of the LPC section.

2 . The gas turbine engine of claim 1 , wherein the bypass air path (BAP) is disposed within a nacelle and is defined by a BAP outer radial structure and a BAP inner radial structure, wherein the exit port is engaged with an exterior surface of the BAP outer radial structure.

3 . The gas turbine engine of claim 1 , wherein the core gas flow path between the compressor inlet and the LPC section is defined by an LPC outer radial structure and an LPC inner radial structure, and wherein the inlet port is engaged with the LPC outer radial structure.

4 . The gas turbine engine of claim 3 , wherein the inlet port includes a scoop that extends radially outward from the LPC outer radial structure and into the core gas path.

5 . The gas turbine engine of claim 1 , further comprising an annular interior compartment that is disposed between the bypass air path and the core gas path, wherein the inlet port is in fluid communication with the interior compartment and the passage that extends through the structural member is in fluid communication with the interior compartment.

6 . The gas turbine engine of claim 5 , wherein the bypass air path (BAP) is disposed with a nacelle and is defined by a BAP outer radial structure and a BAP inner radial structure; and

wherein the core gas flow path (CGFP) between the compressor inlet and the compressor section is defined by a CGFP outer radial structure and a CGFP inner radial structure, and wherein the inlet port is engaged with the CGFP outer radial structure.

7 . The gas turbine engine of claim 6 , wherein the inlet port is engaged with the CGFP outer radial structure at a position forward of the LPC section.

8 . The gas turbine engine of claim 7 , wherein the interior compartment is defined by the BAP inner radial structure, the CGFP outer radial structure, and a firewall that extends between the BAP inner radial structure and the CGFP outer radial structure.

9 . The gas turbine engine of claim 1 , wherein the entrained debris removal system includes a valve controllable between an open configuration and a closed configuration, wherein in the open configuration the valve permits fluid passage through the valve, and in the closed configuration the valve does not permit fluid passage through the valve.

10 . The gas turbine engine of claim 9 , wherein the valve is disposed in line between the passage that extends through the structural member and the exit port.

11 . The gas turbine engine of claim 9 , wherein the valve is disposed in line between the inlet port and the passage that extends through the structural member.

12 . The gas turbine engine of claim 9 , wherein the valve is integrated into the inlet port.

13 . The gas turbine engine of claim 1 , wherein the inlet port is configured as a flush-wall valve.

14 . A gas turbine engine, comprising:

a fan section;

a compressor section that includes a compressor inlet disposed downstream of the fan section;

a combustion section;

a turbine section;

a core gas path that begins at the compressor inlet and extends through the compressor section, the combustion section, and the turbine section;

a bypass air path that is disposed downstream of the fan section and radially outside of the core gas path;

a structural member that extends radially across the bypass air path; and

an entrained debris removal system that includes an inlet port engaged with the core gas path, a passage that extends through the structural member, an exit port that is disposed in contact with ambient air, a valve, and a controller in communication with the valve and a non-transitory memory storing instructions, which instructions when executed cause the controller to selectively operate the valve between an open configuration and a closed configuration, wherein in the open configuration the valve permits fluid passage through the valve, and in the closed configuration the valve does not permit fluid passage through the valve;

wherein the compressor section includes a low pressure compressor (LPC) section; and

wherein the core gas flow path between the compressor inlet and the low pressure compressor is defined by an LPC outer radial structure and an LPC inner radial structure;

wherein the inlet port includes a scoop that extends radially outward from the LPC outer radial structure and into the core gas path.

15 . The gas turbine engine of claim 14 , wherein the bypass air path (BAP) is disposed within a nacelle and is defined by a BAP outer radial structure and a BAP inner radial structure, wherein the exit port is engaged with an exterior surface of the BAP outer radial structure.

16 . A method of removing entrained particles from an airflow within a gas turbine engine, wherein the gas turbine engine includes a fan section, a compressor section that includes a compressor inlet disposed downstream of the fan section, a combustion section, a turbine section, a core gas path that begins at the compressor inlet and extends through the compressor section, the combustion section, and the turbine section, a bypass air path that is disposed downstream of the fan section and radially outside of the core gas path, and a structural member that extends radially across the bypass air path, the method comprising:

providing an inlet port configured to bleed air flow from the core gas path upstream of the compressor section;

providing a fluid passage in fluid communication with the inlet port, the fluid passage extending through the structure member and to an exit port that is disposed in contact with ambient air; and

controlling a valve between an open configuration and a closed configuration, wherein in the open configuration the valve permits fluid passage from the inlet port, through the valve, and out the exit port, and in the closed configuration the valve does not permit fluid passage through the valve;

wherein the bypass air path (BAP) is disposed within a nacelle and is defined by a BAP outer radial structure and a BAP inner radial structure, wherein the exit port is engaged with an exterior surface of the BAP outer radial structure.

17 . The method of claim 16 , wherein the compressor section includes a low pressure compressor (LPC) section; and

wherein the core gas flow path between the compressor inlet and the LPC section is defined by an LPC outer radial structure and an LPC inner radial structure, and wherein the inlet port is engaged with the LPC outer radial structure.