Forward load reduction structures for aft-most stages of high pressure compressors
Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures. The inner circumferential support structure includes an aft-most and forward spacer arms. The compressor also includes two stages, each including a vane having a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and a rotor extending radially from the spacer arm adjacent to the vane. An intersection of the rotors and spacer arms defines centrally located points. An arrangement of a first line extending through the points forms an angle with a second line parallel to a longitudinal centerline and extending through the tips of the vanes. The angle is greater than 0° and less than or equal to 45°.
1 . A compressor, comprising:
an outer circumferential support structure;
an inner circumferential support structure positioned radially inward from the outer circumferential support structure, the inner circumferential support structure comprising an aft-most spacer arm and a forward spacer arm, the outer and inner circumferential support structures arranged concentrically around a longitudinal centerline;
an aft-most stage comprising:
an aft-most vane extending radially inward from the outer circumferential support structure, the aft-most vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
an aft-most rotor extending radially from the aft-most spacer arm adjacent to the aft-most vane, where an intersection of the aft-most rotor and the aft-most spacer arm defines a centrally located first point; and
a forward stage positioned forward of the aft-most stage, the forward stage comprising:
a forward vane extending radially inward from the outer circumferential support structure, the forward vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
a forward rotor extending radially from the forward spacer arm adjacent to the forward vane, where an intersection of the forward rotor and the forward spacer arm defines a centrally located second point,
wherein an arrangement of a first line extending through the first point and the second point forms an angle with a second line extending parallel to the longitudinal centerline and extending through the tip of the aft-most vane and the tip of the forward vane, the angle being greater than 0° and less than or equal to 45°.
2 . The compressor of claim 1 , wherein the angle is greater than 0° less than or equal to 25°.
3 . The compressor of claim 1 , further comprising an aft most stage seal positioned adjacent to the tip of the aft-most vane.
4 . The compressor of claim 3 , wherein the aft most stage seal is a bridge seal, a stick-type seal housing, a box-type seal housing, or incorporates an attached seal ring.
5 . The compressor of claim 1 , wherein the aft-most spacer arm comprises a first portion and a second portion, the first portion coupled to the second portion via a curvic coupling, a friction joint, or a weld joint.
6 . The compressor of claim 1 , wherein the forward spacer arm comprises a first portion and a second portion, the first portion coupled to the second portion via a curvic coupling, a friction joint, or a weld joint.
7 . The compressor of claim 1 , wherein the aft-most stage further comprises a circumferentially bladed disk, an axially bladed disk, or a blisk.
8 . A turbofan engine, comprising:
a fan section; and
a core turbine engine disposed downstream of the fan section, the core turbine engine comprising a compressor,
wherein the compressor comprises:
an outer circumferential support structure;
an inner circumferential support structure positioned radially inward from the outer circumferential support structure, the inner circumferential support structure comprising an aft-most spacer arm and a forward spacer arm, the outer and inner circumferential support structures arranged concentrically around a longitudinal centerline;
an aft-most stage comprising:
an aft-most vane extending radially inward from the outer circumferential support structure, the aft-most vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
an aft-most rotor extending radially from the aft-most spacer arm adjacent to the aft-most vane, where an intersection of the aft-most rotor and the aft-most spacer arm defines a centrally located first point; and
a forward stage positioned forward of the aft-most stage, the forward stage comprising:
a forward vane extending radially inward from the outer circumferential support structure, the forward vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
a forward rotor extending radially from the forward spacer arm adjacent to the forward vane, where an intersection of the forward rotor and the forward spacer arm defines a centrally located second point,
wherein an arrangement of a first line extending through the first point and the second point forms an angle with a second line extending parallel to the longitudinal centerline and extending through the tip of the aft-most vane and the tip of the forward vane, the angle being greater than 0° and less than or equal to 45°.
9 . The turbofan engine of claim 8 , wherein the angle is greater than 0° less than or equal to 25°.
10 . The turbofan engine of claim 8 , wherein the compressor further comprises an aft most stage seal positioned adjacent to the tip of the aft-most vane.
11 . The turbofan engine of claim 10 , wherein the aft most stage seal is a bridge seal, a stick-type seal housing, a box-type seal housing, or incorporates an attached seal ring.
12 . The turbofan engine of claim 8 , wherein the aft-most spacer arm comprises a first portion and a second portion, the first portion coupled to the second portion via a curvic coupling, a friction joint, or a weld joint.
13 . The turbofan engine of claim 8 , wherein the forward spacer arm comprises a first portion and a second portion, the first portion coupled to the second portion via a curvic coupling, a friction joint, or a weld joint.
14 . The turbofan engine of claim 8 , wherein the aft-most stage further comprises a circumferentially bladed disk, an axially bladed disk, or a blisk.