Turbine engine temperature control system with heating element for a gas turbine engine

A turbine engine temperature control system, comprising:

• an outer casing surrounding an airfoil assembly of a gas turbine engine positioned concentrically within the outer casing such that a cavity exists between the outer casing and the airfoil assembly;
• a first air ejector positioned above a horizontally extending centerline of the outer casing to exhaust heated air into the cavity, wherein the first air ejector is formed from a first air ejector body with at least one exhaust orifice positioned in the first air ejector body;
• a second air ejector extending into the cavity to exhaust fluid into the cavity, wherein the second air ejector has at least one exhaust orifice positioned in a second air ejector body;
• wherein the at least one exhaust orifice in the first air ejector body is positioned to emit fluid in a first circumferential direction, and the at least one exhaust orifice in the second air ejector body is positioned to emit fluid in the same circumferential direction to create circumferential fluid flow within the cavity;
• at least one heating element extending into the cavity for heating air within the cavity;
• wherein the at least one heating element is positioned radially inward from an outer surface of the first air ejector body and wherein an exhaust opening of the at least one exhaust orifice first air ejector is positioned in a downstream facing surface;
• and
• a temperature control system configured to emit fluid from the at least one exhaust orifice in the first air ejector body at a different temperature than the at least one exhaust orifice in the second air ejector body.

A turbine engine temperature control system, comprising:

• an outer casing surrounding an airfoil assembly of a gas turbine engine positioned concentrically within the outer casing such that a cavity exists between the outer casing and the airfoil assembly;
• a first air ejector positioned above a horizontally extending centerline of the outer casing to exhaust heated air into the cavity, wherein the first air ejector is formed from a first air ejector body with at least one exhaust orifice positioned in the first air ejector body;
• a second air ejector extending into the cavity to exhaust fluid into the cavity, wherein the second air ejector has at least one exhaust orifice positioned in a second air ejector body;
• wherein the at least one exhaust orifice in the first air ejector body is positioned to emit fluid in a first circumferential direction, and the at least one exhaust orifice in the second air ejector body is positioned to emit fluid in the same circumferential direction to create circumferential fluid flow within the cavity;
• wherein the first air ejector body has a cross-sectional shape when viewed axially that includes a radially outward base surface that is wider than a rounded head and wherein the first air ejector body has a curved upstream surface and a curved downstream surface coupled together with a rounded head.
• at least one heating element extending into the cavity for heating air within the cavity;
• wherein the at least one heating element is positioned radially inward from an outer surface of the first air ejector body and wherein an exhaust opening of the at least one exhaust orifice first air ejector is positioned in a downstream facing surface;
• and
• a temperature control system configured to emit fluid from the at least one exhaust orifice in the first air ejector body at a higher temperature than a temperature of fluid within the cavity.