Blade outer air seal with cooling holes

Patent metadata

Field	Value
Publication number	US-10018068-B2
Application number	US-201514596152-A
Country	US
Kind code	B2
Filing date	Jan 13, 2015
Priority date	Jan 13, 2015
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P′ which is at the center of an arc W′ and co-planer with a machined surface V′.

First claim

What is claimed is:

1. A blade outer air seal (BOAS) for a turbomachine, comprising:
a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V, wherein a coordinate Z originates at point P and bisects arc W, wherein a coordinate Y is perpendicular to surface V, and wherein a coordinate X is orthogonal to Y and Z and wherein the arc W is representative of a circumferential arc of the blade outer air seal.

2. The BOAS of claim 1 , wherein the arc W includes a radius ranging from about 10.16 inches (258.06 millimeters) to about 10.18 inches (258.57 millimeters).

3. A blade outer air seal (BOAS) for a turbomachine, comprising:
a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2, wherein the Cartesian coordinates are provided with respect to a point P′ which is at the center of an arc “W″” and co-planer with a machined surface V′, wherein a coordinate Z′ originates at point P′ and bisects arc W′, wherein a coordinate X′ is perpendicular to surface V′, and wherein a coordinate Y′ is orthogonal to X′ and Z′ and wherein the arc W is representative of a circumferential arc of the blade outer air seal.

4. The BOAS of claim 3 , wherein the arc W′ includes ranging from about 10.25 inches (260.35 millimeters) to about 10.27 inches (260.86 millimeters).

5. A turbomachine, comprising: a turbine section including a plurality of blade outer air seals (BOAS) disposed therein, each of the plurality of BOASs including a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table I or Table 2 and wherein the arc W is representative of a circumferential arc of the blade outer air seal.

6. The turbomachine of claim 5 , wherein the plurality of BOASs includes at least one BOAS having cooling holes defined in at accordance with Table 1, and at least one BOAS having cooling holes defined in at accordance with Table 2.

7. The turbomachine of claim 6 , wherein the at least one BOAS having cooling holes defined in at accordance with Table 1 is disposed in a first stage of the turbine section.

8. The turbomachine of claim 7 , wherein the at least one BOAS having cooling holes defined in at accordance with Table 2 is disposed in a second stage of the turbine section aft of the first stage.

Assignees

• United Technologies Corp

Inventors

• Milligan Peter J
• Lutjen Paul M
• Blaney Ken F
• Dabbs Thurman C
• Ryan Kevin J

Classifications

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/24 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title