TURBINE ENGINE TEMPERATURE CONTROL SYSTEM WITH HEATING ELEMENT FOR A GAS TURBINE ENGINE

• US 20140271152A1
• Filed: 03/13/2013
• Published: 09/18/2014
• Est. Priority Date: 03/13/2013
• Status: Active Grant

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Rodriguez, Jose L.
• Granted Patent: US 9,279,339 B2
• Time in Patent Office: Days
• US Class Current: 415/177
• CPC Class Codes: F01D 21/12 responsive to temperature
• CPC Class Codes: F01D 25/08 Cooling of machines or engines in general F01P; Heating; Heat-insulation of blade-carrying members, of blades F01D5/00
• CPC Class Codes: F01D 25/26 Double casings; Measures against temperature strain in casings
• CPC Class Codes: F05D 2260/601 using an ejector or a jet pump

Abstract

A turbine engine temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine airfoil assembly during shutdown of a gas turbine engine and for preheating an engine during a cold startup is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart. The turbine engine temperature control system may also be used for cold startup conditions to heat engine components such that gaps between turbine airfoil tips and adjacent blade rings can be made larger from thermal expansion, thereby reducing the risk of damage. The turbine engine temperature control system may operate during turning gear system operation after shutdown of the gas turbine engine or during a cold startup.

Claims

1. 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; and

at least one heating element extending into the cavity for heating air within the cavity.

2. The turbine engine temperature control system of claim 1, 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 of the first air ejector is positioned in a downstream facing surface.

3. The turbine engine temperature control system of claim 1, further comprising a fluid flow guide extending laterally such that the at least one heating element is positioned between the fluid flow guide and the first air ejector body to guide the flow of fluid to the at least one heating element.

4. The turbine engine temperature control system of claim 3, wherein the fluid flow guide has a width in a direction that aligned with an axially extending axis that is greater than a width of a base surface of the first air ejector body in the direction.

5. The turbine engine temperature control system of claim 1, 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.

6. The turbine engine temperature control system of claim 5, wherein the curved upstream surface includes a first generally linear base section separated from a generally linear head section by a curved transition section, wherein the generally linear head section is adjacent to the rounded head.

7. The turbine engine temperature control system of claim 1, 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 radially inwardmost point and wherein a base surface of the first air ejector body is curved about an axially extending longitudinal axis and when viewed in a direction aligned with the longitudinal axis.

8. The turbine engine temperature control system of claim 1, wherein the at least one exhaust orifice positioned in the first air ejector body is comprised of a plurality of exhaust orifices positioned closer to a rounded head of the first air ejector body than to a base surface of the first air ejector body.

9. The turbine engine temperature control system of claim 1, wherein the at least one heating element is formed from a plurality of radially extending members extending radially inward between the first air ejector body and a fluid flow guide extending laterally to guide the flow of fluid to the at least one heating element and wherein the plurality of radially extending members are laterally spaced apart enabling fluid to flow therebetween.

10. The turbine engine temperature control system of claim 1, further comprising at least one supply manifold contained within the first air ejector body and in fluid communication with the at least one exhaust orifice and at least one fluid supply system in fluid communication with the at least one supply manifold.

11. The turbine engine temperature control system of claim 1, further comprising 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.

12. The turbine engine temperature control system of claim 11, wherein the second air ejector is positioned below the horizontally extending centerline of the outer casing.

13. The turbine engine temperature control system of claim 11, wherein the first air ejector is positioned at top dead center, and the second air ejector is positioned at bottom dead center.

14. The turbine engine temperature control system of claim 11, 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.

15. The turbine engine temperature control system of claim 11, further comprising 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.

16. 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.

17. The turbine engine temperature control system of claim 16, further comprising a fluid flow guide extending laterally such that the at least one heating element is positioned between the fluid flow guide and the first air ejector body to guide the flow of fluid to the at least one heating element.

18. The turbine engine temperature control system of claim 16, 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.

19. The turbine engine temperature control system of claim 16, wherein the at least one heating element is formed from a plurality of radially extending members extending radially inward between the first air ejector body and a fluid flow guide extending laterally to guide the flow of fluid to the at least one heating elements and wherein the plurality of radially extending members are laterally spaced apart enabling fluid to flow therebetween.

20. 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.