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Blade cooling

a technology of blades and cooling plates, applied in the field of blade cooling, can solve the problems of reducing the pressure differential, increasing the mechanical stress level and the requirement for thicker materials, and adding significantly to the fabrication cost, and achieving the effect of limiting the flow pressure loss of coolan

Inactive Publication Date: 2009-05-28
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The present invention provides a blade cooling arrangement with a coolant gallery and a flow deflector to deflect coolant flow towards a coolant passage opening. This arrangement helps to limit coolant flow pressure loss and improve cooling efficiency. The flow deflector can be adjusted based on temperature or specific requirements, and it can be a curved scoop, a ramp, or a wedge to achieve angular flow overlap. The invention also provides an engine with turbine blades that have the blade cooling arrangement or the flow deflector.

Problems solved by technology

Fabrication of such feed holes in the mounting disk as well as reciprocal holes in the root or connecting end of the blade add significantly to fabrication costs as well as increased mechanical stress levels and their requirement for thicker material.
Unfortunately, coolant flow in a distribution gallery is turned sharply at least twice as it passes to the coolant passage network of the blade.
Such turning can diminish the pressure differential and so flow rate of coolant air into the blade cooling passage network.
Clearly, a reduce flow rate will diminish cooling efficiency and therefore performance.

Method used

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Examples

Experimental program
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first embodiment

[0014]Referring to FIG. 1 illustrating a cooling arrangement in accordance with the present invention. Thus, a mounting hub or disk 11 has a turbine blade 3 secured adjacent to it with a gap or coolant distribution gallery 4 between a mounting or root end 2 of the blade 3 and a top surface 11 of the mounting disk 1. A coolant flow illustrated by broken arrow 5 is drawn into the gallery 4 from a coolant supply system under a positive pressure differential. The gallery 4 has a passage opening 7 which extends to a passage 8 coupled to a coolant passage network within the blade 3 to provide cooling of that blade 3.

[0015]In accordance with the present invention a flow deflector 6 located adjacent and around the opening 7 deflects the coolant flow 5 into the passage 8 through the opening 7. The deflector 6 is substantially flat and creates a wedge or ramp to progressively deflect the coolant flow 5 through the opening 7. In such circumstances, there is less direct or perpendicular collisi...

second embodiment

[0021]FIGS. 2 and 3 illustrate the present invention. Thus, in a similar arrangement to that depicted in FIG. 1 a mounting hub or disk 21 has a turbine blade 23 secured to it with a gap between a blade root end 22 and a top surface 32 of the mounting hub or disk 21. This gap is a coolant gallery 24 through which a coolant flow shown by arrow head 25 passes in order to enter through a passage opening 27 a passage 28 coupled to a coolant passage network of the turbine blade 23. The coolant air flow 25 is deflected by a flow deflector 26 associated and adjacent to the passage opening 27. This flow deflector 26 is located substantially around the passage opening 27 to block the gallery 24 by a close fit association. However, if bypass holes are provided to the respective sides of the deflector 26, coolant air flow 25 can bypass the flow deflector 26 on either side to impinge upon other flow deflectors within the coolant gallery 24.

[0022]The flow deflector 26 has a curved surface 30 whic...

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PUM

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Abstract

In order to couple coolant air flow presented through a coolant gallery 4, 24 through an opening 7, 27 into a passage 8, 28 a flow deflector 6, 26 is provided. The flow deflector 6, 26 progressively deflects the coolant air flow 5, 25 through the opening 7, 27 such that there is reduced loss in coolant flow 5, 25 pressure.

Description

[0001]This is a continuation application of National application Ser. No. 11 / 525,931, filed Sep. 25, 2006 and currently pending, which is a continuation application of National application Ser. No. 10 / 720,333 filed Nov. 25, 2003 which issued on Apr. 3, 2007 under U.S. Pat. No. 7,198,466.FIELD OF THE INVENTION[0002]The present invention relates to blade cooling and more particularly to arrangements for feeding coolant from a mounting disk or hub to turbine blades in a jet engine.BACKGROUND OF THE INVENTION[0003]Cooling of turbine blades in a jet engine is important in order to maintain structural integrity whilst the blades operate at high temperatures approaching if not exceeding the melting point of the materials from which the blades are made. Turbine blades generally include a coolant passage network within their structure within which coolant air circulates in order to cool the blade. Such coolant air must be coupled to the coolant passage network within the blade. Generally, a ...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/18F01D5/08
CPCF01D5/081F01D5/187F05D2260/221F05D2260/60Y02T50/676Y02T50/60
Inventor TOWNES, RODERICK M
Owner ROLLS ROYCE PLC