Gas turbine engine blade outer air seal cooling hole configuration

A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.

BACKGROUND OF THE INVENTION

The present disclosure relates to blade outer air seals (BOAS) for gas turbine engines more particularly to BOAS for gas turbine engines with cooling holes defined therein.

Blade outer air seals (BOAS) can be disposed in turbine sections of turbomachines for sealing the gap between a turbine blade tip and the inner wall of the turbomachine casing. In such uses, the BOAS can be exposed to extreme heat and can require cooling. Accordingly, it is desirable to provide adequate cooling to the BOAS.

SUMMARY

In one exemplary embodiment, a blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.

In a further embodiment of any of the above, the Cartesian coordinate values of Tables 1, 2 and 3 are expressed in inches.

In a further embodiment of any of the above, the reference point is provided on the inner arcuate surface at a midpoint between corners connecting the lateral faces to the inner arcuate surface.

In a further embodiment of any of the above, the Cartesian coordinate values are taken from the reference point relative to a reference plane that is tangent to the reference point. The reference plane is parallel to an engine axis plane that contains an engine axis.

In a further embodiment of any of the above, X values are taken along the reference plane. Positive X values are toward one of the corners and negative X values are toward the other of the corners. Y values are taken in a direction normal to the reference plane. Positive Y values are away from the engine axis and negative Y values are toward the engine axis. Z values are taken along the reference plane in the direction of the engine axis. Positive Z values are toward the forward rail and negative Z values are toward the aft rail.

In a further embodiment of any of the above, Table 1 values correspond to cooling holes on the inner arcuate surface.

In a further embodiment of any of the above, Table 2 values correspond to cooling holes on one of the lateral faces.

In a further embodiment of any of the above, Table 3 values correspond to cooling holes on one of the lateral faces.

In another exemplary embodiment, a blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each of the geometric coordinates is measured from a reference point on the body. Table 1 values correspond to cooling holes on the inner arcuate surface.

In a further embodiment of any of the above, the Cartesian coordinate values of Table 1 are expressed in inches.

In a further embodiment of any of the above, the reference point is provided on the inner arcuate surface at a midpoint between corners connecting the lateral faces to the inner arcuate surface.

In a further embodiment of any of the above, the Cartesian coordinate values are taken from the reference point relative to a reference plane that is tangent to the reference point. The reference plane is parallel to an engine axis plane that contains an engine axis.

In a further embodiment of any of the above, X values are taken along the reference plane. Positive X values are toward one of the corners and negative X values are toward the other of the corners. Y values are taken in a direction normal to the reference plane. Positive Y values are away from the engine axis and negative Y values are toward the engine axis. Z values are taken along the reference plane in the direction of the engine axis. Positive Z values are toward the forward rail and negative Z values are toward the aft rail.

In another exemplary embodiment, a blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2. Each of the geometric coordinates is measured from a reference point on the body. Table 2 values correspond to cooling holes on one of the lateral faces.

In a further embodiment of any of the above, the Cartesian coordinate values of Table 2 are expressed in inches.

In a further embodiment of any of the above, the reference point is provided on the inner arcuate surface at a midpoint between corners connecting the lateral faces to the inner arcuate surface.

In a further embodiment of any of the above, the Cartesian coordinate values are taken from the reference point relative to a reference plane that is tangent to the reference point. The reference plane is parallel to an engine axis plane that contains an engine axis.

In a further embodiment of any of the above, X values are taken along the reference plane. Positive X values are toward one of the corners and negative X values are toward the other of the corners. Y values are taken in a direction normal to the reference plane. Positive Y values are away from the engine axis and negative Y values are toward the engine axis. Z values are taken along the reference plane in the direction of the engine axis. Positive Z values are toward the forward rail and negative Z values are toward the aft rail.

In another exemplary embodiment, a blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2. Each of the geometric coordinates is measured from a reference point on the body. Table 3 values correspond to cooling holes on one of the lateral faces.

In a further embodiment of any of the above, the Cartesian coordinate values of Table 3 are expressed in inches.

In a further embodiment of any of the above, the reference point is provided on the inner arcuate surface at a midpoint between corners connecting the lateral faces to the inner arcuate surface.

In a further embodiment of any of the above, the Cartesian coordinate values are taken from the reference point relative to a reference plane that is tangent to the reference point. The reference plane is parallel to an engine axis plane that contains an engine axis.

In a further embodiment of any of the above, X values are taken along the reference plane. Positive X values are toward one of the corners and negative X values are toward the other of the corners. Y values are taken in a direction normal to the reference plane. Positive Y values are away from the engine axis and negative Y values are toward the engine axis. Z values are taken along the reference plane in the direction of the engine axis. Positive Z values are toward the forward rail and negative Z values are toward the aft rail.

DETAILED DESCRIPTION

Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, an illustrative view of an embodiment of a blade outer air seal (BOAS) in accordance with the disclosure is shown inFIG. 2Aand is designated generally by reference character100. Other embodiments and/or aspects of this disclosure are shown inFIGS. 1, 2B, 3A, 3B, and 4. The systems and methods described herein can be used to provide enhanced cooling for BOAS.

FIG. 1schematically illustrates a gas turbine engine20. The gas turbine engine20is disclosed herein as a two-spool turbofan that generally incorporates a fan section22, a compressor section24, a combustor section26and a turbine section28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section22drives air along a bypass flow path B in a bypass duct defined within a nacelle15, while the compressor section24drives air along a core flow path C for compression and communication into the combustor section26then expansion through the turbine section28.

Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.

Each of the compressor and turbine sections24,28include stages of rotating blades60. A circumferential array of blade outer air seals (BOAS)62are arranged radially outward of the blades60to provide a seal with respect to the blade tips. In the disclosed example, the BOAS62are provided in the first stage of the high pressure turbine54.

Referring toFIGS. 2A and 2B, the BOAS62is provided by a body extending axially in a direction of the engine axis Z between forward and aft rails66,68. The body extends circumferentially between lateral faces74,76to provide an inner arcuate surface64configured to seal relative to a blade tip.

Cooling fluid from a cooling source86, typically bleed air from the compressor section24, is supplied to cooling passages88in the BOAS62that are fluidly connected to multiple cooling holes90. The cooling holes90are illustrated as discrete numbered holes inFIGS. 3-5. The cooling holes90provide boundary layers of cooling fluid to thermally protect the BOAS62from the very high temperatures in the turbine section28.

A reference point R (0, 0, 0) is provided on a reference plane82that is tangent to the inner arcuate surface64. Corners78,80respectively connect the lateral faces74,76to the inner arcuate surface64. The corners78,80are at a distances L from one another. The reference point R is where a plane Y located at a distance ½ L, or the midpoint between the corners78,80, intersects the inner arcuate surface64. The plane Y is normal to the reference plane. The reference plane82is parallel to an engine axis plane84that contains the engine axis Z. X values are taken along the reference plane82, with positive X values toward the corner78and negative X values toward the corner80. Y values are taken in a direction normal to the reference plane82, with positive Y values away from the engine axis Z and negative Y values toward the engine axis Z. Z values are taken along the reference plane82in the direction of the engine axis Z, with positive Z values toward the forward rail66and negative Z values toward the aft rail68.

The cooling holes90extend through an exterior surface of the BOAS62, wherein each of the plurality of film cooling hole's centerline breaks through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3, produced below, wherein each of the geometric coordinates is measured from a reference point R on the BOAS62.

Table 1 values correspond to cooling holes90on the inner arcuate surface64. Table 2 and 3 values correspond to cooling holes90on the lateral faces74,76, respectively. The locations are presented in Tables 1, 2 and 3 in cold, coated, and stationary condition and are subject to change based on finishing of the BOAS62. The coordinates are expressed in inches. One having ordinary skill in the art will appreciate that new locations of cooling holes relative to any suitable reference can be determined in any suitable manner based on the procedures involved in finishing the BOAS62. Holes are located with included part tolerances and a hole true position of about +/−0.020 inches or 0.51 mm. As described herein, cooling holes90can include any suitable cross-sectional shape, such as, but not limited to, circular, elliptical, and/or any other symmetric or non-symmetric shape.

Alternatively, substantial conformance is based on a determination by a national or international regulatory body, for example in a part certification or part manufacture approval (PMA) process for the Federal Aviation Administration, the European Aviation Safety Agency, the Civil Aviation Administration of China, the Japan Civil Aviation Bureau, or the Russian Federal Agency for Air Transport. In these configurations, substantial conformance encompasses a determination that a particular part or structure is identical to, or sufficiently similar to, the specified airfoil, blade, or vane, or that the part or structure is sufficiently the same with respect to a part design in a type-certified or type-certificated BOAS, such that the part or structure complies with airworthiness standards applicable to the specified blade, vane or airfoil. In particular, substantial conformance encompasses any regulatory determination that a particular part or structure is sufficiently similar to, identical to, or the same as a specified BOAS, such that certification or authorization for use is based at least in part on the determination of similarity.

Although the different non-limiting embodiments are illustrated as having specific components, the embodiments of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from any of the non-limiting embodiments in combination with features or components from any of the other non-limiting embodiments.

It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed and illustrated in these exemplary embodiments, other arrangements could also benefit from the teachings of this disclosure.