Gas turbine engine component

Patent metadata

Field	Value
Publication number	US-9518469-B2
Application number	US-201314033900-A
Country	US
Kind code	B2
Filing date	Sep 23, 2013
Priority date	Sep 26, 2012
Publication date	Dec 13, 2016
Grant date	Dec 13, 2016

Abstract

An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes:
determining angles α and β of the directions of cooling air flow into the first and N th rows, respectively; defining a change in angle φ of the direction of cooling air flow between rows as φ=(β−α)/N; and positioning the pedestals such that a line extending forward from the center of each pedestal in the i th row at an angle {α+φ(i−1)} intersects the (i−1) th row at a location which is midway between two neighboring pedestals of the (i−1) th row, i being an integer from 2 to N.

First claim

The invention claimed is:

1. A method of configuring an internally cooled gas turbine engine component,
the component including:
a line of cooling air discharge holes,
an internal cooling channel disposed forward of and extending substantially parallel to the line of discharge holes,
an internal feed cavity disposed between the channel and the line of discharge holes for feeding cooling air from the channel to the discharge holes, and
a plurality of flow disrupting pedestals extending between opposing sides of the feed cavity,
the pedestals being arranged in a number N of rows, which extend substantially parallel to the line of discharge holes, each row of the number N of rows forming flow inlet angles that vary along the length of the rows,
a first row of the number N of rows being located closer to an entrance of the feed cavity than an N th row of the number N of rows, and
remaining rows of the number N of rows being spaced between the first row and the N th row, and the pedestals being spaced apart from each other within each row,

the method including:
determining the flow inlet angle α of a direction of cooling air flow into the first row at one or more radial positions;
determining a flow outlet angle β of the direction of cooling air flow from the N th row;
defining a change in angle φ of the direction of cooling air flow between the rows as φ=(β−α)/N for the one or more radial positions; and
starting from row N, positioning the pedestals such that a line extending forward from the centre of each pedestal in the i th row at an angle {α+φ(i−1)} intersects the (i−1) th row at a location which is midway between two neighbouring pedestals of the (i−1) th row, i being an integer from 2 to N.

2. The method according to claim 1 , wherein the rows are spaced substantially equal distances apart.

3. The method according to claim 1 , wherein the method further includes:
determining the number of pedestals in the N th row such that each pedestal of the N th row corresponds to a respective one of the discharge holes; and
positioning each pedestal of the N th row such that a line extending rearward from the pedestal at the flow outlet angle β coincides with the centre of the respective discharge hole.

4. The method according to claim 1 , wherein N is four or more.

5. The method according to claim 1 , wherein the pedestals are each a column of circular cross-section.

6. The method according to claim 1 , wherein the pedestals are each a column of racetrack-shaped or elliptical cross-section.

7. The method according to claim 6 , wherein the method further includes:
orientating the pedestals such that a long axis of the racetrack-shaped or elliptical cross-section of each pedestal is perpendicular to a line extending forward from the centre of each pedestal in the i th row at an angle {α+φ(i−1)}, i being an integer from 1 to N.

8. The method according to claim 1 , wherein the value of the flow inlet angle α varies along the length of the first row.

9. The method according to claim 1 , wherein the component is a gas turbine aerofoil, the pedestals extending between pressure surface and suction surface sides of the feed cavity.

10. The method according to claim 9 , wherein the line of cooling air discharge holes is a line of slots along a trailing edge of the aerofoil.

11. A process for producing an internally cooled gas turbine engine component, the process including:
configuring the component by performing the method of claim 1 ; and
manufacturing the configured component.

12. An internally cooled gas turbine engine component produced by the process of claim 11 .

13. An internally cooled gas turbine engine component, the component comprising:
a line of cooling air discharge holes,
an internal cooling channel disposed forward of and extending substantially parallel to the line of discharge holes,
an internal feed cavity disposed between the channel and the line of discharge holes for feeding cooling air from the channel to the discharge holes, and
a plurality of flow disrupting pedestals extending between opposing sides of the feed cavity,
the pedestals being arranged in a number N of rows, which extend substantially parallel to the line of discharge holes, each row of the number N of rows forming flow inlet angles that vary along the length of the rows,
a first row of the number N of rows being located closer to an entrance of the feed cavity than an N th row of the number N of rows,
remaining rows of the number N of rows being spaced between the first row and the N th row, and the pedestals being spaced apart from each other within each row,
the first row defining a flow inlet angle α of a direction of cooling air flow into the first row at one or more radial positions,
the N th row defining a flow outlet angle β of the direction of cooling air flow from the N th row,
a change in angle φ of the direction of cooling air flow between the rows being defined as φ=(β−α)/N for the one or more radial positions, and
the pedestals being positioned such that a line extending forward from the centre of each pedestal in the i th row at an angle {α±φ(i−1)} intersects the (i−1) th row at a location which is midway between two neighbouring pedestals of the (i−1) th row, i being an integer from 2 to N,

wherein each pedestal is positioned such that a plurality of streak lines of cooling air advancing on the pedestals split substantially equally to both sides of each pedestal and then substantially completely recombine downstream of each pedestal.

14. The component according to claim 13 , wherein the component is a gas turbine aerofoil, the pedestals extending between pressure surface and suction surface sides of the feed cavity.

15. The component according to claim 14 , wherein the line of cooling air discharge holes is a line of slots along a trailing edge of the aerofoil.

Assignees

• Rolls Royce Plc

Inventors

• Tibbott Ian
• Jackson Dougal Richard

Classifications

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/186 Primary

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

• Y10T29/49336

  Blade making · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title