Internal cooling of engine components

• US 9,797,261 B2
• Filed: 09/04/2015
• Issued: 10/24/2017
• Est. Priority Date: 10/03/2014
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Tibbott, Ian, Ireland, Peter Thomas, Rawlinson, Anthony John, Cresci, Irene
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): Pruitt, Justin
• Application Number:
  US14/846,284
• Publication Number:
  US 20160097286A1
• Time in Patent Office: 781 Days
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2240/126 Baffles or ribs
• CPC Class Codes: F05D 2240/127 Vortex generators, turbulators, or the like, for mixing by creating turbulence F05D2260/2212
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.

Claims

1. A nozzle guide vane or turbine blade of a gas turbine engine, the nozzle guide vane or turbine blade comprising:

at least one internal cooling chamber for passage of cooling air, the at least one cooling chamber including;

(i) a leading edge portion, and (ii) at least one inlet portion through which cooling air enters the at least one cooling chamber from a feed source; and

a partitioning element disposed in the at least one inlet portion of the at least one cooling chamber and extending into the at least one cooling chamber to define a sub-chamber wholly or partly within the at least one cooling chamber, the partitioning element and the leading edge portion constitute boundaries of the sub-chamber, the sub-chamber having an inlet configured to receive cooling air from the feed source, the partitioning element including;

an axially outer portion, relative to a longitudinal axis of the at least one cooling chamber, extending into an inlet feed passage through which cooling air enters the at least one inlet portion of the at least one cooling chamber from the feed source; and

an end portion distal to the inlet feed passage in the at least one cooling chamber bending towards the leading edge portion of the at least one cooling chamber at a short axial distance from the inlet feed passage, such that the partitioning element reduces a cooling air velocity in the sub-chamber to a value smaller than a cooling air velocity in a remainder of the at least one inlet portion of the at least one cooling chamber.

2. The nozzle guide vane or turbine blade as claimed in claim 1, further comprising a forward cooling chamber and a rearward cooling chamber, and the partitioning element is provided in the forward cooling chamber.

3. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the leading edge portion includes a showerhead portion, the sub-chamber defined by the partitioning element being adjacent the showerhead portion.

4. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is mounted in at least the inlet portion of the cooling chamber by being formed integrally with side walls of the nozzle guide vane or turbine blade by casting the partitioning element as an integral internal wall portion of the nozzle guide vane or turbine blade.

5. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is mounted in the inlet portion of the cooling chamber and attached to an inner side wall of the nozzle guide vane or turbine blade.

6. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the cooling chamber contains an insert tube including impingement holes in the insert tube, the impingement holes being configured to feed cooling air to the leading edge portion, and the partitioning element is mounted and attached to an inner side wall of the insert tube.

7. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is a body, plate, wall, member or element having a cross-section or a face adjacent to the leading edge portion.

8. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is provided in the inlet portion of the at least one cooling chamber, whereby a single sub-chamber is defined adjacent the leading edge portion of the at least one cooling chamber.

9. The nozzle guide vane or turbine blade as claimed in claim 1, wherein a plurality of the partitioning elements are provided in at least the inlet portion of the at least one cooling chamber, such that a plurality of sub-chambers are defined in the at least one cooling chamber.

10. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the at least one cooling chamber has a plurality of inlet portions, and each of the plurality of inlet portions is provided with a respective one of a plurality of the partitioning elements.

11. A gas turbine engine including one or more internally cooled nozzle guide vanes or turbine blades, each being the nozzle guide vane or turbine blade as claimed in claim 1.

12. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is mounted in at least the inlet portion of the at least one cooling chamber by manufacturing the partitioning element as a discrete element and subsequently mounting the partitioning element in the nozzle guide vane or turbine blade at a desired location by welding.

13. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is a body, plate, wall, member or element having a cross-section or a face adjacent to the leading edge portion of the at least one cooling chamber, which includes two or more substantially flat sections angled with respect to each other in one or more orthogonal directions.

14. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is a body, plate, wall, member or element having a cross-section or a face adjacent to the leading edge portion of the at least one cooling chamber, which is scoop shaped.

15. The nozzle guide vane or turbine blade as claimed in claim 1, wherein the partitioning element is a body, plate, wall, member or element having a cross-section or a face adjacent to the leading edge portion of the at least one cooling chamber, which is partially cylindrical in at least one orthogonal direction.

16. A method of cooling a leading edge portion of a nozzle guide vane or turbine blade of a gas turbine engine, the nozzle guide vane or turbine blade having at least one internal cooling chamber for passage of cooling air, the least one cooling chamber including a leading edge portion and at least one inlet portion through which cooling air enters the at least one cooling chamber from a feed source, the method comprising:

providing a partitioning element in the inlet portion of the at least one cooling chamber that extends to define a sub-chamber, bound by the partitioning element and the leading edge portion, wholly or partly within the at least one cooling chamber, the sub-chamber having an inlet configured to receive cooling air from the feed source, the partitioning element including;

(i) an axially outer portion, relative to a longitudinal axis of the at least one cooling chamber, extending into an inlet feed passage through which cooling air enters the at least one inlet portion of the cooling chamber from the feed source; and

(ii) an end portion distal to the inlet feed passage in the at least one cooling chamber bending towards the leading edge portion of the at least one cooling chamber at a short axial distance from the inlet feed passage, such that the partitioning element reduces a cooling air velocity in the sub-chamber to a value smaller than a cooling air velocity in a remainder of the at least one inlet portion of the at least one cooling chamber; and

when in use, cooling the nozzle guide vane or turbine blade by feeding cooling air from the feed source into both the sub-chamber and the remainder of the at least one cooling chamber.