Turbine blade equipped with means of adjusting its cooling fluid flow rate

Patent metadata

Field	Value
Publication number	US-9353634-B2
Application number	US-200913125257-A
Country	US
Kind code	B2
Filing date	Oct 16, 2009
Priority date	Oct 22, 2008
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

A turbine blade cooled by an automatically variable internal flow of cooling fluid. The blade includes orifices situated under the blade root via which the cooling fluid penetrates, and an adjustment plate including holes situated in register with the orifices, the adjustment plate having a coefficient of expansion that is different from the coefficient of expansion of the blade root.

First claim

The invention claimed is:

1. A turbine blade cooled by an internal flow of cooling fluid entering via orifices situated beneath a blade root, comprising:
an adjustment plate including holes situated in register with the orifices; and
a metal calibration plate provided at a bottom portion of the blade root, the metal calibration plate including the orifices defined therein which are in correspondence with the holes in the adjustment plate,
wherein a fluid flow section is defined by an amount of coincidence between the orifices situated beneath the blade root and the holes included in the adjustment plate,
wherein the adjustment plate is made of a material having a coefficient of expansion different from a coefficient of expansion of a material constituting the metal calibration plate, and
wherein the adjustment plate is mounted under the blade root with longitudinal guidance and is fastened in a manner that conserves a possibility of relative movement between the holes in the adjustment plate and the orifices in the blade root such that the fluid flow section increases with temperature due to a difference between the coefficient of expansion of the material of the adjustment plate and the coefficient of the material constituting the metal calibration plate.

2. A turbine blade according to claim 1 , wherein the blade is a moving blade.

3. A turbine blade according to claim 1 , wherein the adjustment plate is made of a material having a coefficient of expansion that is less than the coefficient of expansion of a material of the blade root.

4. A turbine blade according to claim 1 , wherein the adjustment plate is made of a ceramic material, having a coefficient of expansion that is smaller than the coefficient of expansion of the blade root.

5. A turbine blade according to claim 1 , wherein the adjustment plate is made of a composite material, having a coefficient of expansion that is smaller than the coefficient of expansion of the blade root.

6. A turbine blade according to claim 1 , wherein the adjustment plate is fastened at only one of its ends to the blade root.

7. A turbine blade according to claim 1 , wherein the adjustment plate is engaged in a rectilinear guide secured to the blade root.

8. A turbine blade according to claim 1 , wherein the orifices situated under the blade root are triangular in shape.

9. A turbine blade according to claim 1 , wherein the holes in the adjustment plate are square or rectangular in shape.

10. A turbine comprising:
a disk; and
blades;
the disk including slots in its periphery, each slot receiving a blade root, air being channeled to the slots,
wherein each blade is in accordance with claim 1 .

11. A turbine blade according to claim 1 , wherein the adjustment plate is engaged in a rectilinear guide secured to the calibration plate.

12. A turbine blade according to claim 1 , wherein the adjustment plate is planar and a bottom of the blade root which abuts the adjustment plate is planar.

13. A turbine blade according to claim 1 , wherein the orifices beneath the blade root are aligned in a lengthwise direction of the blade root, the orifices flowing along internal cavities so as to be exhausted via multiple outlet orifices opening out into a surface of an airfoil of the turbine blade.

14. A turbine blade according to claim 1 , wherein the adjustment plate is fastened to the blade root by an anchor element at only one end of the adjustment plate.

15. A turbine according to claim 10 , as a high pressure turbine of an airplane turbojet.

Assignees

• Grohens Regis
• Royan Renaud Gabriel Constant
• Snecma

Inventors

• Grohens Regis
• Royan Renaud Gabriel Constant

Classifications

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2300/50212

  dissimilar · CPC title

• F05D2250/11

  triangular · CPC title

• G05D23/025

  the sensing element being placed within a regulating fluid flow · CPC title