Blade cooling and sealing system

a gas turbine engine and sealing technology, applied in the direction of liquid fuel engines, vessel construction, marine propulsion, etc., can solve the problems of affecting engine performance, unable to generate useful work, and air that is bled from the compressor prior to combustion (i.e. air that has bypassed), and achieves the effect of less air
US20130028735A1Inactive Publication Date: 2013-01-31ROLLS ROYCE PLC
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Patent Information

Authority / Receiving Office
US · United States
Patent Type
Applications(United States)
Current Assignee / Owner
ROLLS ROYCE PLC
Publication Date
2013-01-31
Estimated Expiration
Not applicable · inactive patent

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Abstract

A cooled component for a gas turbine engine, for example a turbine rotor blade, is provided. The component has an internal cooling flow passage. Cooling air is passed through the internal cooling flow passage to remove heat from the component and thereby reduce its temperature. The cooling air is bled from the internal cooling passage after it has passed through a portion of the passage into an internal bleed flow passage. This bled air is then used in a seal. Thus, some of the cooling air that enters the internal cooling flow passage is used both to cool the component and to form a seal, for example with another component.
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Description

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application is based upon and claims the benefit of priority from British Patent Application Number 1112880.8 filed 27 Jul. 2011, the entire contents of which are incorporated by reference.BACKGROUND OF THE INVENTION

[0002] 1. Field of the Invention

[0003] The present invention concerns cooling and sealing arrangements in a gas turbine engine. In particular, the present invention concerns a method and apparatus for using flow to cool components in a gas turbine engine and seal between components of a gas turbine engine.

[0004] 2. Description of the Related Art

[0005] The performance of a gas turbine engine, for example measured in terms of efficiency or specific output, may be improved by increasing the turbine gas temperature. It is therefore generally desirable to operate the turbine at the highest possible temperature. For a given gas turbine configuration (for example in terms of engine cycle compression ratio or bypass ratio), increasin...

Claims

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