Monolithic superstructure for gas turbine engines
The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.
1 . A monolithic superstructure to support a rotor of a gas turbine engine, the monolithic superstructure comprising:
a compressor flange to be coupled to an axial end of a compressor case of the gas turbine engine;
a mounting tab to be coupled to a frame supporting the gas turbine engine;
an outer case including a diffuser case portion extending between the compressor flange and the mounting tab;
an aero component support; and
an aero component connected to the outer case via the aero component support, the aero component including a diffuser portion, the diffuser portion longitudinally and radially aligned with the rotor when the diffuser portion is at a first temperature, the diffuser portion longitudinally and radially aligned with the rotor when the diffuser portion is at a second temperature, the second temperature at least 200 degrees Fahrenheit greater than the first temperature, wherein a first load path between the aero component and the mounting tab extends through the aero component support without extending through the diffuser case portion, and a second load path between the compressor flange and the mounting tab extends through the diffuser case portion without extending through the aero component support.
2 . The monolithic superstructure of claim 1 , wherein the aero component further includes deswirler tubes and a back wall swirl plate.
3 . The monolithic superstructure of claim 2 , wherein the deswirler tubes and the diffuser portion define a flow path between the rotor and a combustor of the gas turbine engine.
4 . The monolithic superstructure of claim 2 , wherein the aero component support extends between the deswirler tubes and the outer case.
5 . The monolithic superstructure of claim 2 , wherein the deswirler tubes include air extraction ports to connect the deswirler tubes to a turbine cooling passage.
6 . The monolithic superstructure of claim 5 , wherein the turbine cooling passage extends between the aero component and an accelerator.
7 . The monolithic superstructure of claim 2 , wherein the rotor is an impeller.
8 . The monolithic superstructure of claim 7 , wherein the deswirler tubes include a lateral curvature in an opposite direction of a direction of movement of the impeller.
9 . The monolithic superstructure of claim 1 , wherein the rotor and the diffuser portion are spaced a dimension at the first temperature, the dimension maintained within 10% when the diffuser portion is at the second temperature.
10 . The monolithic superstructure of claim 1 , wherein the aero component support is to allow radial movement of the aero component and to resist longitudinal movement of the aero component.
11 . A monolithic superstructure comprising:
a bearing portion to be coupled to a shaft of a gas turbine engine;
an aero component including a diffuser portion radially aligned with a rotor coupled to the shaft;
a compressor flange to be coupled to an axial end of a compressor case of the gas turbine engine;
a mounting tab to be coupled to a frame supporting the gas turbine engine;
a diffuser case portion extending between the compressor flange and the mounting tab;
a first load transferring portion extending between the bearing portion and the aero component;
a second load transferring portion extending between the mounting tab and the aero component; and
wherein the bearing portion, the first load transferring portion, the aero component, the second load transferring portion, and the mounting tab sequentially define a first load path between the shaft and the frame, wherein the first load path extends through the second load transferring portion between the aero component and the mounting tab without extending through the diffuser case portion, and a second load path between the compressor flange and the mounting tab extends through the diffuser case portion without extending through the second load transferring portion.
12 . The monolithic superstructure of claim 11 , wherein the first load transferring portion is conical.
13 . The monolithic superstructure of claim 11 , wherein the bearing portion includes:
bearing supports adjacent to the first load transferring portion;
a sump sealing surface extending radially inward from the bearing supports; and
a turbine mounting surface to be coupled to a turbine case of the gas turbine engine.
14 . The monolithic superstructure of claim 11 , wherein the bearing portion further including a turbine cooling passage defined between the first load transferring portion, the aero component, and an inner combustor shroud.
15 . The monolithic superstructure of claim 11 , further including an outer case including:
the diffuser case portion; and
a combustor case portion, the mounting tab disposed between the diffuser case portion and the combustor case portion.
16 . The monolithic superstructure of claim 15 , wherein the aero component includes a plurality of deswirler tubes extending from the diffuser portion to a plurality of deswirler outlets within the combustor case portion.
17 . The monolithic superstructure of claim 11 , wherein the compressor flange is radially aligned with the diffuser portion.
18 . The monolithic superstructure of claim 11 , wherein a flow path through the monolithic superstructure extends through the aero component.