COOLED COMPRESSOR
An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions. At least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction. An example compressor including the spacer is also disclosed.
1 . A method of cooling a compressor section of a gas turbine engine, comprising:
diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction; and
moving the flow from the heat exchanger back to the compressor in a second direction.
2 . The method of claim 1 , further comprising the step of removing a first amount of thermal energy from the flow by the heat exchanger.
3 . The method of claim 2 , further comprising the step of removing a second amount of thermal energy from the flow by the heat exchanger, the second amount different from the first amount.
4 . The method of claim 1 , wherein the flow moves from the heat exchanger to a rim of an aftmost stage of the compressor.
5 . The method of claim 1 , wherein the first direction is an axial direction and the second direction is an axial direction opposite from the first axial direction.
6 . The method of claim 5 , further comprising the step of moving a portion of the flow from the heat exchanger to a compressor hub in the first axial direction.
7 . The method of claim 1 , wherein the flow is diverted from a midpoint of a core airflow through the compressor.
8 . A spacer for a compressor of a gas turbine engine, comprising:
a first side portion;
a second side portion spaced apart from the first side portion; and
a middle web arranged between the first and second side portions, wherein at least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction.
9 . The spacer of claim 8 , wherein the middle web includes at least one orifice to communicate flow in a direction that is opposite from the core flowpath flow direction.
10 . The spacer of claim 8 , wherein one of the first and second side portions includes at least one orifice in a direction that is perpendicular to the core flowpath direction.
11 . The spacer of claim 8 , wherein the at least one orifice include a valve, the valve configured to vary a flowrate of the flow through the at least one orifice.
12 . The spacer of claim 8 , wherein the flow is radially inside a core flowpath of the compressor.
13 . The spacer of claim 8 , wherein the first side portion is parallel to the second side portion.
14 . A compressor for a gas turbine engine, comprising:
a first compressor stage;
a second compressor stage; and
a spacer arranged between the first and second compressor stages, the spacer including a first side portion; a second side portion spaced apart from the first side portion; and a middle web arranged between the first and second side portions, wherein at least one of the first and second side portions and the middle web includes at least one orifice.
15 . The compressor of claim 14 , wherein one of the first and second compressor stages is the aftmost compressor stage of a high pressure compressor.
16 . The compressor of claim 14 , wherein the spacer is received between first and second rims of the first and second compressor stages, respectively.
17 . The compressor of claim 14 , wherein the at least one orifice includes a valve, the valve configured to vary a flowrate of the flow through the at least one orifice.
18 . The compressor of claim 14 , wherein the first side portion is arranged radially outward from the second side portion.
19 . The compressor of claim 18 , wherein the second side portion and the middle web include first and second orifices, respectively.
20 . The compressor of claim 18 , wherein the first and second side portions and the middle web include first and second sets of orifices, respectively.