Cooled component for the turbine of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9518468-B2
Application number	US-201213359180-A
Country	US
Kind code	B2
Filing date	Jan 26, 2012
Priority date	Feb 17, 2011
Publication date	Dec 13, 2016
Grant date	Dec 13, 2016

Abstract

A component for the turbine of a gas turbine engine is provided. The component two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions which form a multi-pass cooling passage within the component. The passage portions are connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring of the passage portions. The component further includes one or more core tie linking passages formed in the divider members. One or more differential pressure reducing arrangements are formed in the multi-pass cooling passage adjacent respective of the core tie linking passages.

First claim

The invention claimed is:

1. A component for a turbine of a gas turbine engine, the component comprising:
two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side and generally elongate cooling fluid passage portions forming a multi-pass cooling passage within the component, the passage portions being connected in a series fluid flow relationship by respective bends formed by joined ends of neighboring cooling fluid passage portions;
one or more core tie linking passages formed in the divider members, and at least one core tie linking passage having an entrance at an upstream passage portion and an exit at a neighboring downstream passage portion to allow cooling fluid to leak therethrough to bypass the bend formed by the joined ends of the neighboring passage portions; and
one or more differential pressure reducing arrangements formed in the multi-pass cooling passage facing a respective one of the core tie linking passages and the one or more differential pressure reducing arrangements extending at least partially across the entrance of the one of the core tie linking passages, the one or more differential pressure reducing arrangements being configured to reduce the difference in the static pressure of the cooling fluid between the entrance of the respective core tie linking passage and the exit of the core tie linking passage, the one or more differential pressure reducing arrangements including a flow deflector structure in the upstream passage portion, and the flow deflector structure being configured to substantially locally remove a dynamic component of the cooling fluid flow in the upstream passage portion at the entrance of the core tie linking passage, wherein:
the flow deflector structure defines a cavity in the upstream passage portion at the entrance of the core tie linking passage, and
the flow deflector structure is configured to define a one hundred and eighty degree bend for flow of coolant air from the upstream passage portion to the cavity.

2. The component according to claim 1 , further comprising:
a flow decelerating formation in the downstream passage portion, the flow decelerating formation being arranged to decrease the velocity of the cooling fluid flow in the downstream passage portion at the exit of the core tie linking passage.

3. The component according to claim 2 , wherein the flow decelerating formation includes one or more flow splitting members in the downstream passage portion, the one or more flow splitting members interconnecting the facing walls and extending in the direction of flow of the cooling fluid to form, on a longitudinal cross-section through the aerofoil portion, an elongate island around which the cooling fluid flow splits in the downstream passage portion.

4. The component according to claim 3 , wherein the flow decelerating formation includes a flow blocking structure in the downstream passage portion at the downstream side of the exit of the core tie linking passage, the flow blocking structure being arranged to convert the dynamic component of the cooling fluid flow in the downstream passage portion at the exit of the core tie linking passage into an increased static pressure.

5. The component according to claim 2 , wherein the flow decelerating formation includes a flow blocking structure in the downstream passage portion at the downstream side of the exit of the core tie linking passage, the flow blocking structure being arranged to convert the dynamic component of the cooling fluid flow in the downstream passage portion at the exit of the core tie linking passage into an increased static pressure.

6. The component according to claim 1 , which is an aerofoil blade or vane, the two facing walls being the suction side and the pressure side walls of the aerofoil portion of the blade or vane.

7. A gas turbine engine having one or more components according to claim 1 .

Assignees

• Tibbott Ian
• Jackson Dougal R
• Rolls Royce Plc

Inventors

• Tibbott Ian
• Jackson Dougal R

Classifications

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D9/06

  Fluid supply conduits to nozzles or the like · CPC title