Method of clearance control for an interdigitated turbine engine
The present disclosure is directed to a method of operating an active clearance control system for an interdigitated turbine engine. The method includes flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine. The present disclosure is further directed to a gas turbine engine including a low speed turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The engine further includes a turbine frame at least partially surrounding the low speed turbine rotor; a seal assembly disposed between the outer shroud of the low speed turbine rotor and the turbine frame; and a fifth manifold coupled to the turbine frame. The fifth manifold provides a pressurized flow of air to the seal assembly.
1. A method of operating an active clearance control system for an interdigitated turbine engine, the method comprising:
flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and
adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine;
flowing air from a pressure plenum at a combustion section to a turbine bearing, the turbine bearing comprising an outer air bearing and an inner air bearing;
flowing air between the outer air bearing of the turbine bearing and a turbine rotor hub, the turbine rotor hub connected to the interdigitated turbine section;
flowing air between the inner air bearing of the turbine bearing and a shaft; and
flowing air from the turbine bearing to a pressure regulating valve.
2. The method of claim 1 , wherein adjusting the flow of air to the rotatable outer shroud is based at least on an exhaust gas temperature at the interdigitated turbine section and a first rotational speed of the outer shroud.
3. The method of claim 2 , wherein the interdigitated turbine section comprises a first turbine rotor rotatable at the first rotational speed at least partially different from a second turbine rotor rotatable at a second rotational speed, and wherein adjusting the flow of air is further based on the second rotational speed of the second turbine rotor interdigitated with the first turbine rotor including the outer shroud.
4. The method of claim 3 , wherein adjusting the flow of air to the rotatable outer shroud further comprises:
determining a desired clearance gap between the outer shroud and a radially outward end of a plurality of second turbine airfoils of the second turbine rotor.
5. The method of claim 3 , wherein adjusting the flow of air to the outer shroud further comprises:
determining a desired radial gap between a seal assembly and the outer shroud; and
determining a desired axial gap between the seal assembly and the outer shroud.
6. The method of claim 3 , wherein adjusting the flow of air to the outer shroud further comprises:
pressurizing a first side of a seal assembly, wherein pressurizing the first side of the seal assembly provides a flow of air between the outer shroud and the seal assembly.
7. The method of claim 1 , further comprising:
flowing air from the compressor section to a second turbine rotor interdigitated with a plurality of outer shroud airfoils of the rotatable outer shroud of a first turbine rotor of the interdigitated turbine section.
8. The method of claim 7 , wherein flowing air to the second turbine rotor comprises flowing air to an inner diameter of the second turbine rotor to attenuate radial thermal growth.
9. The method of claim 6 , wherein pressurizing the first side of the seal assembly comprises pressurizing an aspirating face seal assembly between the rotatable outer shroud and a turbine frame.
10. The method of claim 1 , further comprising:
operating the gas turbine engine to provide a flow of air through a primary flowpath and a secondary flowpath;
directing at least a first portion of the flow of air to a seal assembly between the rotatable outer shroud and a turbine frame; and
directing at least a second portion of the flow of air along a longitudinal direction of and around a circumference of the rotatable outer shroud based on one or more engine operating conditions.
11. The method of claim 10 , further comprising:
directing at least a third portion of air to the second turbine rotor, wherein the second turbine rotor is positioned radially inward of the rotatable outer shroud, and wherein the third portion of air provides thermal attenuation at the second turbine rotor to mitigate radial growth of the second turbine rotor.
12. The method of claim 1 , further comprising:
determining a desired flow or pressure of air at one or more of the outer shroud of a first turbine rotor or a second turbine rotor of the interdigitated turbine section based on one or more of a lookup table, a transfer function, and a curve comprising at least a function of a radial dimension of the outer shroud of the first turbine rotor and the second turbine rotor relative to one or more of a first rotational speed of the outer shroud, a second rotational speed of the second turbine rotor, an exhaust gas temperature, a first material thermal expansion constant relative to the outer shroud, and a second material thermal expansion constant relative to the second turbine rotor.
13. The method of claim 1 , comprising:
providing a first supply of air from between the outer air bearing and the turbine rotor hub to a manifold; and
providing a second supply of air from between the inner air bearing and the shaft to the manifold.