Fan load tension structural guide vane with bypass cooling cavities
A fan exit guide vane with a load member and cooling cavity including an inner attachment region opposite an outer attachment region; a load member cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane from the inner attachment region to the outer attachment region; the load member extending through the load member cavity beyond each of the inner attachment region and the outer attachment region of the fan exit guide vane; and a cooling cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the inner attachment region and the outer attachment region.
1 . A fan exit guide vane with a load member and a cooling cavity comprising:
a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane;
a load member cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane from the radially inner attachment region to the radially outer attachment region;
the load member extending through the load member cavity beyond each of the radially inner attachment region and the radially outer attachment region of the fan exit guide vane;
the cooling cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region; and
a heat exchanger thermally coupled to the cooling cavity.
2 . The fan exit guide vane with the load member and the cooling cavity according to claim 1 , wherein the load member being configured to support a load path in tension along the span dimension of the fan exit guide vane between the radially inner attachment region spanwise and the radially outer attachment region; and the cooling cavity being configured to support heat transfer from a working fluid to a fan bypass flow.
3 . The fan exit guide vane with the load member and the cooling cavity according to claim 1 , further comprising:
electronics thermally coupled to the cooling cavity.
4 . The fan exit guide vane with the load member and the cooling cavity according to claim 1 , further comprising:
a working fluid pipe thermally coupled to the cooling cavity.
5 . The fan exit guide vane with the load member and the cooling cavity according to claim 1 , wherein the cooling cavity encloses a predetermined volume of the fan exit guide vane, the predetermined volume enclosed by the cooling cavity being greater than a normal volume of the fan exit guide vane responsive to the load member accounting for a structural tension load that would otherwise be required to be maintained by material of the fan exit guide vane occupying a space to form the cooling cavity.
6 . The fan exit guide vane with the load member and the cooling cavity according to claim 1 , further comprising:
an acoustic treatment formed on a face sheet attached to the pressure side between the leading edge and trailing edge; the face sheet enclosing the cooling cavity.
7 . A gas turbine engine with a fan exit guide vane with a load member and a cooling cavity comprising:
a fan located within a fan duct;
an array of fan exit guide vanes supported within the fan duct downstream from the fan, the array of fan exit guide vanes span across the fan duct attached to a radially inner surface of the fan duct and a radially outer surface of the fan duct;
each of the fan exit guide vanes comprising a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region, the radially inner attachment region in operative communication with the radially inner surface of the fan duct, the radially outer attachment region in operative communication with the radially outer surface of the fan duct; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane;
a load member cavity formed within at least one fan exit guide vane in the array, the load member cavity extending spanwise through the at least one fan exit guide vane from the radially inner attachment region to the radially outer attachment region;
the load member extending through the load member cavity beyond each of the radially inner attachment region and the radially outer attachment region of the at least one fan exit guide vane; the load member in operative communication with the radially inner surface and the radially outer surface;
the cooling cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region; and
a heat exchanger thermally coupled to the cooling cavity.
8 . The gas turbine engine with a fan exit guide vane with a load member and the cooling cavity according to claim 7 , wherein the load member being configured to support a load path in tension along the span dimension of the at least one fan exit guide vane between the radially inner surface spanwise and the radially outer surface of the fan duct, and the cooling cavity being configured to support heat transfer from a working fluid and/or electronics to a fan bypass flow.
9 . The gas turbine engine with a fan exit guide vane with a load member and the cooling cavity according to claim 7 , further comprising:
electronics thermally coupled to the cooling cavity.
10 . The gas turbine engine with a fan exit guide vane with a load member and the cooling cavity according to claim 7 , further comprising:
a working fluid pipe thermally coupled to the cooling cavity.
11 . The gas turbine engine with a fan exit guide vane with a load member and the cooling cavity according to claim 7 , wherein the array of the fan exit guide vanes includes at least one of a symmetrically aligned circular pattern of vanes with a cooling cavity and an asymmetrically aligned circular pattern of vanes with a cooling cavity.
12 . A process for supporting a structural load path in a gas turbine engine with a fan exit guide vane having a load member and cooling cavity comprising:
locating a fan within a fan duct;
supporting an array of fan exit guide vanes within the fan duct downstream from the fan;
attaching the array of fan exit guide vanes spanned across the fan duct to a radially inner surface of the fan duct and a radially outer surface of the fan duct;
each of the fan exit guide vanes comprising a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region;
coupling the radially inner attachment region in operative communication with the radially inner surface of the fan duct;
coupling the radially outer attachment region in operative communication with the radially outer surface of the fan duct;
a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane;
forming a load member cavity within at least one fan exit guide vane in the array;
extending the load member cavity spanwise through the at least one fan exit guide vane from the radially inner attachment region to the radially outer attachment region;
extending the load member through the load member cavity beyond each of the radially inner attachment region and the radially outer attachment region of the at least one fan exit guide vane;
coupling the load member in operative communication with the radially inner surface and the radially outer surface; and
forming the cooling cavity within the fan exit guide vane extending spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region; and
thermally coupling a heat exchanger to the cooling cavity.
13 . The process of claim 12 , further comprising:
configuring the load member to support a load path in tension along the span dimension of the at least one fan exit guide vane between the radially inner surface spanwise and the radially outer surface of the fan duct; and
configuring the cooling cavity to support heat transfer from a working fluid and/or electronics to a fan bypass flow.
14 . The process of claim 12 , further comprising:
thermally coupling electronics to the cooling cavity.
15 . The process of claim 12 , further comprising:
inserting the load member within the array of fan exit guide vanes with at least one of a symmetrically aligned circular pattern and an asymmetrically aligned circular pattern; and
inserting at least one of the heat exchanger, electronics and working fluid pipe within the array of fan exit guide vanes with at least one of a symmetrically aligned circular pattern and an asymmetrically aligned circular pattern.
16 . The process of claim 12 , further comprising:
thermally coupling a working fluid pipe to the cooling cavity.
17 . The process of claim 12 , further comprising:
enclosing a predetermined volume of the fan exit guide vane for the cooling cavity, the predetermined volume of the cooling cavity being greater than a normal volume responsive to the load member accounting for a structural tension load that would otherwise be required to be maintained by material of the fan exit guide vane occupying a space to form the cooling cavity.