Fluid flow assembly

Patent metadata

Field	Value
Publication number	US-10415416-B2
Application number	US-201615260701-A
Country	US
Kind code	B2
Filing date	Sep 9, 2016
Priority date	Sep 9, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.

First claim

What is claimed is:

1. A fluid flow assembly comprising:
an orifice plate comprising a plurality of sets of orifices; and a plurality of plenums defined by a blade outer air seal;
wherein each set of orifices of the plurality of sets of orifices is aligned with and in fluid communication with a respective plenum of the plurality of plenums;
wherein a dimension of the orifice plate, in a direction parallel to a cross-section of a first set of orifices of the plurality of sets of orifices and along an axial up or downstream surface of the orifice plate, is comparatively less than a circular diameter of a single orifice having a cross-sectional area that equals a cumulative cross-sectional area of the first set of orifices.

2. The fluid flow assembly of claim 1 , wherein each set of orifices of the plurality of sets of orifices comprises three orifices.

3. The fluid flow assembly of claim 1 , wherein the orifice plate and the blade outer air seal are annular, wherein the plurality of sets of orifices are distributed circumferentially relative to each other and the plurality of plenums are distributed circumferentially relative to each other.

4. The fluid flow assembly of claim 1 , wherein the orifice plate is mounted to a vane outer support.

5. The fluid flow assembly of claim 1 , wherein each orifice in each set of orifices of the plurality of sets of orifices comprises a uniform cross-sectional area and a uniform cross-sectional shape.

6. The fluid flow assembly of claim 1 , wherein the blade outer air seal comprises a fluid chamber configured to be in fluid receiving communication with the plurality of plenums.

7. A gas turbine engine comprising:
a vane outer support comprising an orifice plate, wherein the orifice plate comprises a plurality of sets of orifices; and
a blade outer air seal defining a plurality of plenums;
wherein each set of orifices of the plurality of sets of orifices is forward relative to, and substantially axially aligned with, a respective plenum of the plurality of plenums;
wherein a dimension of the orifice plate, in a direction parallel to a cross-section of a first set of orifices of the plurality of sets of orifices and along an axial up or downstream surface of the orifice plate, is comparatively less than a circular diameter of a single orifice having a cross-sectional area that equals a cumulative cross-sectional area of the first set of orifices.

8. The gas turbine engine of claim 7 , wherein a set of orifices of the plurality of sets of orifices comprises three orifices.

9. The gas turbine engine of claim 7 , wherein each orifice of a set of orifices of the plurality of sets of orifices comprises a uniform cross-sectional area.

10. The gas turbine engine of claim 7 , wherein each orifice of a set of orifices of the plurality of sets of orifices is radially equidistant from an engine central longitudinal axis of the gas turbine engine.

11. The gas turbine engine of claim 7 , wherein a set of orifices of the plurality of sets of orifices is circular.

12. The gas turbine engine of claim 7 , wherein the orifice plate extends substantially radially.

13. The gas turbine engine of claim 12 , wherein the dimension is a radial dimension, wherein the radial dimension of the orifice plate is comparatively less than the diameter of the single orifice having the cross-sectional area that equals the cumulative cross-sectional area of the first set of orifices of the plurality of sets of orifices.

14. The gas turbine engine of claim 7 , wherein the plurality of sets of orifices are distributed circumferentially relative to each other.

15. The gas turbine engine of claim 7 , wherein the blade outer air seal comprises a plurality of fluid chambers aft of and in fluid receiving communication with the plurality of plenums.

16. The gas turbine engine of claim 15 , wherein a first pressure of fluid forward of the vane outer support is higher than a second pressure of fluid in the plurality of fluid chambers.

Assignees

• United Technologies Corp

Inventors

• Clark Thomas E
• Mclaughlin Brian C

Classifications

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F01D11/12 Primary

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2220/32

  in gas turbines · CPC title