POWER TURBINE AIR STRUT
A power turbine section for a gas turbine engine includes an inlet case along an axis. An inlet duct within the inlet case is along the axis and an air strut is mounted to the inlet case transverse to the axis to extend through the inlet duct, the air strut includes a multiple of passages.
1 . A power turbine section for a gas turbine engine comprising:
an inlet case along an axis;
an inlet duct within said inlet case along said axis; and
an air strut mounted to said inlet case transverse to said axis to extend through said inlet duct, said air strut including more than one passage.
2 . The power turbine section as recited in claim 1 , wherein said more than one passage includes a first passage and a second passage.
3 . The power turbine section as recited in claim 2 , further comprising a wall that separates said first passage from said second passage.
4 . The power turbine section as recited in claim 3 , wherein said wall is a longitudinal wall.
5 . The power turbine section as recited in claim 3 , wherein said wall is a lateral wall.
6 . The power turbine section as recited in claim 1 , wherein at least one passage of said more than one passage is circular in cross-section.
7 . The power turbine section as recited in claim 1 , wherein at least one passage of said more than one passage is triangular in cross-section.
8 . A gas turbine engine comprising:
a gas generator section; and
a power turbine section driven by said gas generator section, said power turbine section including an inlet duct through which an air strut extends, said air strut including more than one passage.
9 . The gas turbine engine as recited in claim 8 , wherein said multiple of passages include a first passage and a second passage.
10 . The gas turbine engine as recited in claim 9 , wherein said first passage and said second passage are in communication with a compressor section of said gas generator section.
11 . The gas turbine engine as recited in claim 10 , wherein said first passage is in communication with a first stage of said compressor section and said second passage is in communication with a second stage of said compressor section, said first stage different than said second stage.
12 . The gas turbine engine as recited in claim 10 , further comprising a wall that separates said first passage from said second passage.
13 . The gas turbine engine as recited in claim 12 , wherein said wall is a longitudinal wall.
14 . The gas turbine engine as recited in claim 12 , wherein said wall is a lateral wall.
15 . The gas turbine engine as recited in claim 10 , wherein at least one of said multiple of passages are circular in cross-section.
16 . The gas turbine engine as recited in claim 10 , wherein at least one of said multiple of passages is triangular in cross-section.
17 . A method of communicating a cooling airflow to a power turbine, comprising:
communicating a first cooling airflow from a compressor section through an air strut; and
communicating a second cooling airflow from the compressor section through the air strut.
18 . The method as recited in claim 17 , wherein the first cooling airflow is at a different pressure than the second cooling airflow.
19 . The method as recited in claim 17 , wherein the first cooling airflow is at a different temperature than the second cooling airflow.
20 . The method as recited in claim 17 , wherein the first cooling airflow is communicated to a compartment adjacent to a bearing support.