Patent Description:
A gas turbine engine includes various fluid cooled components such as turbine blades and turbine vanes. Such fluid cooled components may include one or more cooling apertures extending through a sidewall of the respective component. Various cooling aperture types and configurations are known in the art. While these known cooling apertures have various benefits, there is still room in the art for improvement.

<CIT> discloses a prior art apparatus according to the preamble of claim <NUM>.

According to an aspect of the present disclosure, an apparatus is provided for a turbine engine according to claim <NUM>.

The following optional features may be applied to the above aspect:
The meter section may extend within the wall from the inlet to the transition section. The diffuser section may extend within the wall from the transition section to the outlet.

The transition section may laterally taper as the transition section extends within the wall from the diffuser section to the meter section.

The meter section may meet the transition section at an interface. A cross-sectional geometry of the meter section at the interface may be different than a cross-sectional geometry of the transition section at the interface.

A shape of the cross-sectional geometry of the meter section at the interface may be different than a shape of the cross-sectional geometry of the transition section at the interface.

A dimension of the cross-sectional geometry of the meter section at the interface may be different than a corresponding dimension of the cross-sectional geometry of the transition section at the interface.

The diffuser section may meet the transition section at a second interface. The diffuser section and the transition section may share a common cross-sectional geometry at the second interface.

A centerline of the diffuser section may be laterally misaligned with a centerline of the meter section.

A centerline of the transition section may be laterally aligned with the centerline of the diffuser section.

The sidewall may include a substrate and an outer coating applied over the substrate. The meter section and the transition section may be formed in the substrate. The diffuser section may be formed in the substrate and the outer coating.

The sidewall may also include an inner coating between the outer coating and the substrate. The diffuser section may also be formed in the inner coating.

The diffuser section may be configured as or otherwise include a single lobe diffuser section.

The diffuser section may be configured as or otherwise include a multi-lobe diffuser section.

The turbine engine component may be configured as an airfoil for the turbine engine.

The turbine engine component may be configured as a flowpath sidewall for the turbine engine.

The present disclosure includes fluid cooled components of a gas turbine engine. For ease of description, the turbine engine may be described below as a turbofan turbine engine. The present disclosure, however, is not limited to such an exemplary gas turbine engine. The turbine engine, for example, may alternatively be configured as a turbojet turbine engine, a turboprop turbine engine, a turboshaft turbine engine, a propfan turbine engine, a pusher fan turbine engine or an auxiliary power unit (APU) turbine engine. The turbine engine may be configured as a geared turbine engine or a direct drive turbine engine. The present disclosure is also not limited to aircraft applications. The turbine engine, for example, may alternatively be configured as a ground-based industrial turbine engine for power generation, or any other type of turbine engine which utilizes fluid cooled components.

<FIG> is a side cutaway illustration of the turbofan turbine engine <NUM>. This turbine engine <NUM> extends along an axial centerline <NUM> between a forward, upstream airflow inlet <NUM> and an aft, downstream airflow exhaust <NUM>. The turbine engine <NUM> includes a fan section <NUM>, a compressor section <NUM>, a combustor section <NUM>, a turbine section <NUM> and an exhaust section <NUM> (partially shown in <FIG>). The compressor section <NUM> includes a low pressure compressor (LPC) section 29A and a high pressure compressor (HPC) section 29B. The turbine section <NUM> includes a high pressure turbine (HPT) section 31A and a low pressure turbine (LPT) section 31B.

The engine sections <NUM>-<NUM> are arranged sequentially along the axial centerline <NUM> within an engine housing <NUM>. This engine housing <NUM> includes an inner case <NUM> (e.g., a core case) and an outer case <NUM> (e.g., a fan case). The inner case <NUM> may house one or more of the engine sections 29A-31B; e.g., an engine core. The outer case <NUM> may house at least the fan section <NUM>.

Each of the engine sections <NUM>, 29A, 29B, 31A and 31B includes a respective rotor <NUM>-<NUM>. Each of these rotors <NUM>-<NUM> includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks. The rotor blades, for example, may be formed integral with or mechanically fastened, welded, brazed, adhered and/or otherwise attached to the respective rotor disk(s).

The fan rotor <NUM> is connected to a gear train <NUM>, for example, through a fan shaft <NUM>. The gear train <NUM> and the LPC rotor <NUM> are connected to and driven by the LPT rotor <NUM> through a low speed shaft <NUM>. The HPC rotor <NUM> is connected to and driven by the HPT rotor <NUM> through a high speed shaft <NUM>. The shafts <NUM>-<NUM> are rotatably supported by a plurality of bearings <NUM>; e.g., rolling element and/or thrust bearings. Each of these bearings <NUM> is connected to the engine housing <NUM> by at least one stationary structure such as, for example, an annular support strut.

During operation, air enters the turbine engine <NUM> through the airflow inlet <NUM>. This air is directed through the fan section <NUM> and into a core flowpath <NUM> and a bypass flowpath <NUM>. The core flowpath <NUM> extends sequentially through the engine sections 29A-<NUM>. The air within the core flowpath <NUM> may be referred to as "core air". The bypass flowpath <NUM> extends through a bypass duct, which bypasses the engine core. The air within the bypass flowpath <NUM> may be referred to as "bypass air".

The core air is compressed by the LPC rotor <NUM> and the HPC rotor <NUM> and directed into a combustion chamber <NUM> of a combustor in the combustor section <NUM>. This fuel air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor <NUM> and the LPT rotor <NUM> to rotate. The rotation of the HPT rotor <NUM> and the LPT rotor <NUM> respectively drive rotation of the HPC rotor <NUM> and the LPC rotor <NUM> and, thus, compression of the air received from a core airflow inlet. The rotation of the LPT rotor <NUM> also drives rotation of the fan rotor <NUM>, which propels bypass air through and out of the bypass flowpath <NUM>.

The turbine engine <NUM> includes a plurality of fluid cooled components (e.g., 60AH; generally referred to as "<NUM>") arranged within, for example, the combustor section <NUM>, the turbine section <NUM> and/or the exhaust section <NUM>. Examples of these fluid cooled components <NUM> include airfoils such as, but not limited to, a rotor blade airfoil (e.g., 60A, 60D) and a stator vane airfoil (e.g., 60B, 60C, <NUM>). Other examples of the fluid cooled components <NUM> include flowpath walls such as, but not limited to, a combustor wall (e.g., 60F), an exhaust duct wall (e.g., 60E), a shroud or other flowpath wall (e.g., <NUM>), a rotor blade platform and a stator vane platform. Of course, various other fluid cooled components may be included in the turbine engine <NUM>, and the present disclosure is not limited to any particular types or configurations thereof.

<FIG> illustrates a portion of one of the fluid cooled components <NUM> within the turbine engine <NUM>. This fluid cooled component <NUM> has a component wall <NUM> (e.g., a sidewall or an endwall) configured with one or more cooling apertures <NUM>.

Referring to <FIG>, the component wall <NUM> has a thickness <NUM> that extends vertically (e.g., along a z-axis) between and to a first surface <NUM> and a second surface <NUM>. The component first surface <NUM> may be configured as an interior and/or a cold side surface of the component wall <NUM>. The component first surface <NUM>, for example, may at least partially form a peripheral boundary of a cooling fluid volume <NUM> (e.g., a cavity or a passage) along the component wall <NUM>. The component first surface <NUM> may thereby be subject to relatively cool fluid (e.g., cooling air) supplied to the cooling fluid volume <NUM>. This cooling fluid volume <NUM> may be an internal volume formed within the fluid cooled component <NUM> where, for example, the component is an airfoil. Alternatively, the cooling fluid volume <NUM> may be an external volume formed external to the fluid cooled component <NUM> where, for example, the component is a flowpath wall. The component second surface <NUM> may be configured as an exterior and/or a hot side surface of the component wall <NUM>. The component second surface <NUM>, for example, may at least partially form a peripheral boundary of a portion of, for example, the core flowpath <NUM> along the component wall <NUM>. The component second surface <NUM> may thereby be subject to relative hot fluid (e.g., combustion products) flowing through the core flowpath <NUM> within, for example, one of the engine sections <NUM>-<NUM> of <FIG>.

The component wall <NUM> of <FIG> includes a component substrate <NUM> and one or more external component coatings <NUM> and <NUM>. The component substrate <NUM> at least partially or completely forms and carries the component first surface <NUM>. The component substrate <NUM> has a thickness <NUM> that extends vertically (e.g., along the z-axis) between and to the component first surface <NUM> and a second surface <NUM> of the component substrate <NUM>. This substrate second surface <NUM> may be configured as an exterior surface of the component substrate <NUM> prior to being (e.g., partially or completely) covered by the one or more component coatings <NUM> and <NUM>. The substrate thickness <NUM> may be greater than one-half (<NUM>/<NUM>) of the wall thickness <NUM>. The substrate thickness <NUM>, for example, may be between two-third (<NUM>/<NUM>) and four-fifths (<NUM>/<NUM>) of the wall thickness <NUM>.

The component substrate <NUM> is constructed from substrate material <NUM>. This substrate material <NUM> may be an electrically conductive material. The substrate material <NUM>, for example, may be or otherwise include metal. Examples of the metal include, but are not limited to, nickel (Ni), titanium (Ti), aluminum (Al), chromium (Cr), cobalt (Co), and alloys thereof. The metal, for example, may be a nickel or cobalt based superalloy such as, but not limited to, Pratt and Whitney Aircraft alloy PWA <NUM> or Pratt and Whitney Aircraft alloy PWA <NUM>.

The inner coating <NUM> may be configured as a bond coating between the component substrate <NUM> and the outer coating <NUM>. The inner coating <NUM> of <FIG> is bonded (e.g., directly) to the substrate second surface <NUM>. The inner coating <NUM> at least partially or completely covers the substrate second surface <NUM> (e.g., along an x-y plane of <FIG>). The inner coating <NUM> has a thickness <NUM> that extends vertically (e.g., along the z-axis) between and to component substrate <NUM> and the outer coating <NUM>. This inner coating thickness <NUM> may be less than one-seventh (<NUM>/<NUM>) of the wall thickness <NUM>. The inner coating thickness <NUM>, for example, may be between one-eighth (<NUM>/<NUM>) and one-fortieth (<NUM>/<NUM>) of the wall thickness <NUM>.

The inner coating <NUM> is constructed from inner coating material <NUM>. This inner coating material <NUM> may be an electrically conductive material. The inner coating material <NUM>, for example, may be or otherwise include metal. Examples of the metal include, but are not limited to, MCrAlY and MAlCrX, where "M" is nickel (Ni), cobalt (Co), iron (Fe) or any combination thereof, and where "Y" or "X" is hafnium (Hf), yttrium (Y), silicon (Si) or any combination thereof. The MCrAlY and MAlCrX may be further modified with strengthening elements such as, but not limited to, tantalum (Ta), rhenium (Re), tungsten (W), molybdenum (Mo) or any combination thereof. An example of the MCrAlY is Pratt and Whitney Aircraft alloy PWA <NUM>.

The inner coating <NUM> may be formed from a single layer of the inner coating material <NUM>. The inner coating <NUM> may alternatively be formed from a plurality of layers of the inner coating material <NUM>, where the inner coating material <NUM> within each of those inner coating layers may be the same as one another or different from one another.

The outer coating <NUM> may be configured as a protective coating for the component substrate <NUM> and, more generally, the fluid cooled component <NUM>. The outer coating <NUM>, for example, may be configured as a thermal barrier layer and/or an environmental layer. The outer coating <NUM> at least partially or completely forms and carries the component second surface <NUM>. The outer coating <NUM> of <FIG> is bonded (e.g., directly) to a second (e.g., exterior) surface <NUM> of the inner coating <NUM>. The outer coating <NUM> at least partially or completely covers the inner coating second surface <NUM> as well as the underlying substrate second surface <NUM> (e.g., along an x-y plane of <FIG>). The outer coating <NUM> has a thickness <NUM> that extends vertically (e.g., along the z-axis) between and to the inner coating <NUM> and the component second surface <NUM>. This outer coating thickness <NUM> may be less than one-half (<NUM>/<NUM>) of the wall thickness <NUM>. The outer coating thickness <NUM>, for example, may be between one-third (<NUM>/<NUM>) and one-eighth (<NUM>/<NUM>) of the wall thickness <NUM>. The outer coating thickness <NUM>, however, may be greater than the inner coating thickness <NUM>.

The outer coating <NUM> is constructed from outer coating material <NUM>. This outer coating material <NUM> may be a non-electrically conductive material. The outer coating material <NUM>, for example, may be or otherwise include ceramic. Examples of the ceramic include, but are not limited to, yttria stabilized zirconia (YSZ) and gadolinium zirconate (GdZ). The outer coating material <NUM> of the present disclosure is not limited to non-electrically conductive materials. In other embodiments, for example, the outer coating material <NUM> may be an electrically conductive material; e.g., metal.

The outer coating <NUM> may be formed from a single layer of the outer coating material <NUM>. The outer coating <NUM> may alternatively be formed from a plurality of layers of the outer coating material <NUM>, where the outer coating material <NUM> within each of those outer coating layers may be the same as one another or different from one another. For example, the outer coating <NUM> may include a thin interior layer of the YSZ and a thicker exterior later of the GdZ.

Each of the cooling apertures <NUM> extends along a respective longitudinal centerline <NUM> between and to an inlet <NUM> of the respective cooling aperture <NUM> and an outlet <NUM> of the respective cooling aperture <NUM>. The cooling aperture inlet <NUM> of <FIG> is located in the component first surface <NUM>. The cooling aperture inlet <NUM> thereby fluidly couples its respective cooling aperture <NUM> with the cooling fluid volume <NUM> along the component first surface <NUM>. The cooling aperture outlet <NUM> of <FIG> is located in the component second surface <NUM>. The cooling aperture outlet <NUM> thereby fluidly couples its respective cooling aperture <NUM> with the core flowpath <NUM> along the component second surface <NUM>.

Each of the cooling apertures <NUM> may include a meter section <NUM>, a diffuser section <NUM> and a transition section <NUM>. The meter section <NUM> is disposed at (e.g., on, adjacent or proximate) the cooling aperture inlet <NUM>. The meter section <NUM> is configured to meter (e.g., regulate) a flow of cooling fluid flowing from the cooling fluid volume <NUM>, through the substrate material <NUM>, to the diffuser section <NUM>. The diffuser section <NUM> is disposed at the cooling aperture outlet <NUM>. The diffuser section <NUM> is configured to diffuse the cooling fluid exhausted (e.g., directed out) from the cooling aperture outlet <NUM> into, for example, a film for cooling a downstream portion of the component second surface <NUM>. The transition section <NUM> is disposed longitudinally along the longitudinal centerline <NUM> between and fluidly coupled with the meter section <NUM> and the diffuser section <NUM>. The transition section <NUM> is configured to accommodate a certain degree of (e.g., lateral) misalignment between the meter section <NUM> and the diffuser section <NUM>.

Misalignment may occur between different sections / portions of a cooling aperture where those cooling aperture sections are formed using different machining processes and/or at different stages. For example, misalignment may occur between the meter section <NUM> and the diffuser section <NUM> of a respective cooling aperture <NUM> where the diffuser section <NUM> is formed using a first machining process (e.g., a laser machining process) and the meter section <NUM> is formed using a second machining process (e.g., electrical discharge machining (EDM) process) that is different than the first machining process. Following formation of the diffuser section <NUM> with the first machining process, for example, a tool for the first machining process may be moved away and a tool for the second machining process may be positioned in its place (or, the component <NUM> may be moved from a first machining process location to a second machining process location). This swapping of the tools (or, movement of the component <NUM>) may open the manufacturing process up to slight misalignments due to, for example, tool manipulator tolerances, etc. An unexpected misalignment may cause an undesirable flow disturbance between the meter section <NUM> and the diffuser section <NUM>. The transition section <NUM> of the present disclosure, however, may accommodate a slight misalignment between the meter section <NUM> and the diffuser section <NUM> as discussed below in further detail. The transition section <NUM> may thereby reduce effects of misalignment between the meter section <NUM> and the diffuser section <NUM>.

The meter section <NUM> of <FIG> extends longitudinally along the longitudinal centerline <NUM> within (e.g., partially into) the component substrate <NUM>. More particularly, the meter section <NUM> extends longitudinally along a meter segment <NUM> of the longitudinal centerline <NUM> (e.g., a centerline of the meter section <NUM>) from the cooling aperture inlet <NUM> to an outlet <NUM> of the meter section <NUM>. The meter section outlet <NUM> of <FIG> is disposed vertically within the component substrate <NUM> intermediately between the component first surface <NUM> and the substrate second surface <NUM>. The meter section outlet <NUM> of <FIG> is thereby vertically recessed into the component substrate <NUM> by a vertical distance <NUM> (e.g., along the z-axis).

The longitudinal centerline <NUM> and its (e.g., entire) meter segment <NUM> of <FIG> are angularly offset from the component first surface <NUM> by an included angle <NUM>. This meter segment angle <NUM> may be an acute angle, or a right angle. The meter segment angle <NUM>, for example, may be between ten degrees (<NUM>°) and eighty degrees (<NUM>°); e.g., between twenty degrees (<NUM>°) and thirty degrees (<NUM>°).

The meter section <NUM> has a longitudinal length measured along the meter segment <NUM> between the cooling aperture inlet <NUM> and the meter section outlet <NUM>.

Referring to <FIG>, the meter section <NUM> has a first lateral width 116A (e.g., a major axis dimension; e.g., along the y-axis) and a second lateral width 116B (e.g., a minor axis dimension; e.g., along the x-axis). These lateral widths 116A and 116B may be measured, for example, along / within a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. The first lateral width 116A of <FIG> is greater than the second lateral width 116B. However, in other embodiments, the first lateral width 116A may be equal to or less than the second lateral width 116B.

The meter section <NUM> has a cross-sectional geometry when viewed, for example, in a (e.g., x-y plane) plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the plane of <FIG>. This meter section cross-sectional geometry may be uniform (e.g., remain constant) along the longitudinal length of the meter section <NUM>. The meter section cross-sectional geometry of <FIG> has a rounded shape. Examples of the rounded shape include, but are not limited to, an oval, an ellipse and a circle. The present disclosure, however, is not limited to the foregoing exemplary meter section cross-sectional geometry shapes.

The diffuser section <NUM> of <FIG> extends longitudinally along the longitudinal centerline <NUM> out of the component substrate <NUM>, through the inner coating <NUM> and the outer coating <NUM>. More particularly, the diffuser section <NUM> of <FIG> extends longitudinally along a diffuser segment <NUM> of the longitudinal centerline <NUM> (e.g., a centerline of the diffuser section <NUM>) from an inlet <NUM> of the diffuser section <NUM>, through the materials <NUM>, <NUM> and <NUM>, to the cooling aperture outlet <NUM>. The diffuser section inlet <NUM> of <FIG> is disposed vertically within the component substrate <NUM> intermediately between the component first surface <NUM> and the substrate second surface <NUM>. The diffuser section inlet <NUM> of <FIG> is thereby vertically recessed into the component substrate <NUM> by a vertical distance <NUM> (e.g., along the z-axis), which vertical distance <NUM> is less than the vertical distance <NUM>.

The longitudinal centerline <NUM> and its (e.g., entire) diffuser segment <NUM> of <FIG> are angularly offset from the component second surface <NUM> by an included angle <NUM>. This diffuser segment angle <NUM> may be an acute angle. The diffuser segment angle <NUM>, for example, may be between twenty degrees (<NUM>°) and eighty degrees (<NUM>°); e.g., between thirty-five degrees (<NUM>°) and fifty-five degrees (<NUM>°). The diffuser segment angle <NUM> of <FIG> is different (e.g., less) than the meter segment angle <NUM>. The diffuser segment <NUM> may thereby be angularly offset from the meter segment <NUM>.

The diffuser section <NUM> has a longitudinal length measured along the diffuser segment <NUM> between the diffuser section inlet <NUM> and the cooling aperture outlet <NUM>. This diffuser section longitudinal length may be equal to or different (e.g., less or greater) than the meter section longitudinal length.

Referring to <FIG>, the diffuser section <NUM> has a first lateral width 124A (e.g., a major axis dimension; e.g., along the y-axis) and a second lateral width 124B (e.g., a minor axis dimension; e.g., along the x-axis). These lateral widths 124A and 124B (generally referred to as "<NUM>") may be measured, for example, along / within a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. The first lateral width 124A of <FIG> is greater than the second lateral width 124B. However, in other embodiments, the first lateral width 124A may be equal to or less than the second lateral width 124B.

The first lateral width 124A at the diffuser section inlet <NUM> of <FIG> may be equal to (or different than) the corresponding first lateral width 116A at the meter section outlet <NUM> (see <FIG>). The second lateral width 124B at the diffuser section inlet <NUM> of <FIG> may also or alternatively be equal to (or different than) the corresponding second lateral width 116B at the meter section outlet <NUM> (see <FIG>). However, the lateral widths <NUM> of the diffuser section <NUM> at other locations along the longitudinal centerline <NUM> may be greater the corresponding lateral widths 116A/116B of the meter section <NUM>. More particularly, the diffuser section <NUM> of <FIG> (see also transition from <FIG>) laterally diverges as the diffuser section <NUM> projects longitudinally away from the meter section <NUM> (and the transition section <NUM>) towards or to the cooling aperture outlet <NUM>.

Referring to <FIG>, the diffuser section <NUM> has a cross-sectional geometry when viewed, for example, in a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. At the diffuser section inlet <NUM>, the diffuser section cross-sectional geometry may be the same as the meter section cross-sectional geometry at the meter section outlet <NUM> (see <FIG>). The diffuser section cross-sectional geometry of <FIG>, for example, has a rounded shape. Examples of the rounded shape include, but are not limited to, an oval, an ellipse and a circle. The present disclosure, however, is not limited to the foregoing exemplary diffuser section cross-sectional geometry shapes. Furthermore, in other embodiments, the diffuser section cross-sectional geometry (e.g., its size and/or shape) at the diffuser section inlet <NUM> may be different than the meter section cross-sectional geometry at the meter section outlet <NUM>.

Referring to <FIG>, <FIG>, a shape and/or dimensions of the diffuser section cross-sectional geometry change as the diffuser section <NUM> projects longitudinally away from the meter section <NUM> (and the transition section <NUM>), e.g. sequentially through the materials <NUM>, <NUM> and <NUM> of <FIG>, to the cooling aperture outlet <NUM>. For example, at the cooling aperture outlet <NUM> of <FIG>, the diffuser section cross-sectional geometry may have a complex shape when viewed, for example, in a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. This diffuser section cross-sectional geometry of <FIG> includes a (e.g., curved or straight) leading edge section <NUM>, a (e.g., curved or straight) trailing edge section <NUM> and opposing (e.g., curved or straight; concave, convex and/or splined) sidewall sections 132A and 132B (generally referred to as "<NUM>"). Each of the sidewall sections <NUM> extends between and to respective ends of the leading and the trailing edge sections <NUM> and <NUM>. A lateral width of the leading edge section <NUM> may be different (e.g., smaller) than a lateral width of the trailing edge section <NUM>. The sidewall sections <NUM> may thereby generally laterally diverge away from one another as the sidewall sections <NUM> extend from the leading edge section <NUM> to the trailing edge section <NUM>.

In some embodiments, referring to <FIG>, the diffuser section <NUM> may be configured as a single lobe diffuser section. In other embodiments, referring to <FIG>, the diffuser section <NUM> may be configured as a multi-lobe diffuser section. Various other single lobe and multi-lobe diffuser sections for cooling apertures are known in the art, and the present disclosure is not limited to any particular ones thereof. Further details on various multi-lobe diffuser sections can be found in <CIT>.

The transition section <NUM> of <FIG> extends longitudinally along the longitudinal centerline <NUM> within the component substrate <NUM> between and to the meter section <NUM> and the diffuser section <NUM>. More particularly, the transition section <NUM> of <FIG> extends longitudinally along a transition segment <NUM> of the longitudinal centerline <NUM> (e.g., a centerline of the transition section <NUM>) from the meter section outlet <NUM> (e.g., a meter-transition section interface), through the substrate material <NUM>, to the diffuser section inlet <NUM> (e.g., a diffuser-transition section interface).

The transition segment <NUM> of <FIG> may follow a trajectory of and/or may be parallel (e.g., coaxial) with the meter segment <NUM>. However, in other embodiments, the transition segment <NUM> may follow a trajectory of and/or may be parallel (e.g., coaxial) with the diffuser segment <NUM>, or otherwise.

The transition section <NUM> has a longitudinal length measured along the transition segment <NUM> between the meter section outlet <NUM> and the diffuser section inlet <NUM>. This transition section longitudinal length may be different (e.g., less) than meter section longitudinal length and/or the diffuser section length.

Referring to <FIG>, the transition section <NUM> has a first lateral width 136A (e.g., a major axis dimension; e.g., along the y-axis) and a second lateral width 136B (e.g., a minor axis dimension; e.g., along the x-axis). These lateral widths 136A and 136B (generally referred to as "<NUM>") may be measured, for example, along / within a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. The first lateral width 136A of <FIG> is greater than the second lateral width 136B. However, in other embodiments, the first lateral width 136A may be equal to or less than the second lateral width 136B.

Referring still to <FIG>, the first lateral width 136A at the meter section outlet <NUM> (see <FIG>) may be different (e.g., greater) than the corresponding first lateral width 116A at the meter section outlet <NUM> (see <FIG>) and/or the corresponding first lateral width 124A at the diffuser section inlet <NUM> (see <FIG>). The second lateral width 136B at the meter section outlet <NUM> may also or alternatively be different (e.g., greater) than the corresponding second lateral width 116B at the meter section outlet <NUM> (see <FIG>) and/or corresponding the second lateral width 124B at the diffuser section inlet <NUM> (see <FIG>). However, referring to <FIG>, the first lateral width 136A at the diffuser section inlet <NUM> may be equal to (or different than) the corresponding first lateral width 116A at the meter section outlet <NUM> (see <FIG>) and/or the corresponding first lateral width 124A at the diffuser section inlet <NUM> (see <FIG>). The second lateral width 136B at the diffuser section inlet <NUM> may also or alternatively be equal to (or different than) the corresponding second lateral width 116B at the meter section outlet <NUM> (see <FIG>) and/or the corresponding second lateral width 124B at the diffuser section inlet <NUM> (see <FIG>). The transition section <NUM> of <FIG> (see also transition from <FIG>) laterally diverges as the transition section <NUM> projects longitudinally away from the diffuser section <NUM> towards the meter section <NUM>. Referring to <FIG>, with the foregoing configuration, a footprint <NUM> of the meter section <NUM> at the meter section outlet <NUM> may fit within a footprint <NUM> of the transition section <NUM> at the meter section outlet <NUM>, where the footprints <NUM> and <NUM> are viewed in a common plane; e.g., a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>.

Referring to <FIG>, the transition section <NUM> has a cross-sectional geometry when viewed, for example, in a plane parallel with the component first surface <NUM> and/or the component second surface <NUM>; e.g., the x-y plane. At the diffuser section inlet <NUM> (see <FIG>), the transition section cross-sectional geometry may be the same as the diffuser section cross-sectional geometry (see <FIG>). The transition section cross-sectional geometry of <FIG>, for example, has a rounded shape. Examples of the rounded shape include, but are not limited to, an oval, an ellipse and a circle. The present disclosure, however, is not limited to the foregoing exemplary transition section cross-sectional geometry shapes. The transition section cross-sectional geometry at the diffuser section inlet <NUM> may also be the same as the meter section cross-sectional geometry at the meter section outlet <NUM> (see <FIG>).

Referring to <FIG>, <FIG>, a shape and/or dimensions of the transition section cross-sectional geometry change as the transition section <NUM> projects longitudinally away from the meter section <NUM> to the diffuser section <NUM>. For example, at the meter section outlet <NUM> of <FIG>, the footprint <NUM> of the transition section cross-sectional geometry is configured to (e.g., completely) circumscribe / envelope / overlap the footprint <NUM> of the meter section <NUM>. As described above, the transition section cross-sectional geometry may be dimensioned greater than the meter section cross-sectional geometry at the meter section outlet <NUM>. In addition or alternatively, the transition section cross-sectional geometry may be selectively shaped different than the meter section cross-sectional geometry at the meter section outlet <NUM>.

The size and/or the shape of the transition section cross-sectional geometry at the meter section outlet <NUM> may be tailored to accommodate slight (e.g., forward or backward) lateral misalignment (e.g., along the y-axis) as shown, for example, in <FIG>. Here, the transition segment <NUM> and/or the diffuser segment <NUM> may be laterally offset from the meter segment <NUM> by a lateral distance 140A, 140B (e.g., along the y-axis). The size and/or the shape of the transition section cross-sectional geometry at the meter section outlet <NUM> may also or alternatively be tailored to accommodate slight (e.g., side-to-side) lateral misalignment (e.g., along the x-axis) as shown, for example, in <FIG>. Here, the transition segment <NUM> and/or the diffuser segment <NUM> may be laterally offset from the meter segment <NUM> by a lateral distance 142A, 142B (e.g., along the x-axis). The size and/or the shape of the transition section cross-sectional geometry at the meter section outlet <NUM> may also or alternatively be tailored to accommodate more lateral misalignment in one direction than another direction as shown, for example, in <FIG>.

Referring to <FIG>, the transition section <NUM> forms an annular groove <NUM> within the sidewall <NUM>. This groove <NUM> extends circumferentially about (e.g., partially or completely around) the longitudinal centerline <NUM>. The groove <NUM> extends laterally into the substrate material <NUM> to a groove end surface <NUM>. The groove <NUM> extends longitudinally within the substrate material <NUM> between the meter section <NUM> and its outlet <NUM> and the diffuser section <NUM> and its inlet <NUM>. The groove <NUM> abuts longitudinally against / is formed by an annular shoulder <NUM> (e.g., a shelf, a ledge, a rim, etc.) formed at an interface <NUM> between the transition section <NUM> and the meter section <NUM>. The groove <NUM> of <FIG> may facilitate complete (e.g., relatively unobstructed) fluid communication from the meter section <NUM> to the diffuser section <NUM> through the transition section <NUM> even where, for example, the meter section <NUM> and the diffuser section <NUM> are slightly misaligned; e.g., the meter segment <NUM> is laterally offset from and/or non-coincident with the diffuser segment <NUM> (see <FIG>).

<FIG> illustrate an exemplary sequence of steps for forming the cooling aperture <NUM>. Referring to <FIG>, the diffuser section <NUM> is formed (e.g., laser machined) in the fluid cooled component <NUM> and its sidewall <NUM>. Referring to <FIG>, the transition section <NUM> is formed (e.g., laser machined) in the fluid cooled component <NUM> and its sidewall <NUM>. The forming of at least a portion (or an entirety) of the transition section <NUM> may be performed concurrently with (e.g., at a tail end of) the formation of the diffuser section <NUM>. Alternatively, the transition section <NUM> may be formed during a separate process step from the formation of the diffuser section <NUM>. <FIG> also illustrates exemplary energy beam paths 152A and 152B for forming an outer peripheral portion of the transition section <NUM>. Referring to <FIG>, the meter section <NUM> is formed (e.g., electrical discharge machined) in the fluid cooled component <NUM> and its sidewall <NUM>. Of course, various other formation processes may be used to at least partially or completely form any one or more of the sections <NUM>, <NUM> and/or <NUM>.

Claim 1:
An apparatus for a turbine engine (<NUM>), comprising:
a turbine engine component (<NUM>) including a sidewall (<NUM>) and a cooling aperture (<NUM>);
the cooling aperture (<NUM>) including an inlet (<NUM>), an outlet (<NUM>), a meter section (<NUM>), a diffuser section (<NUM>) and a transition section (<NUM>) between and fluidly coupled with the meter section (<NUM>) and the diffuser section (<NUM>), and the cooling aperture (<NUM>) extending through the sidewall (<NUM>) from the inlet (<NUM>) to the outlet (<NUM>);
the meter section (<NUM>) at the inlet (<NUM>);
the diffuser section (<NUM>) at the outlet (<NUM>); and
the transition section (<NUM>) configured to accommodate lateral misalignment between the meter section (<NUM>) and the diffuser section (<NUM>);
characterised in that:
the transition section (<NUM>) forms an annular groove (<NUM>) within the sidewall (<NUM>), and the annular groove (<NUM>) abuts longitudinally against or is formed by an annular shoulder (<NUM>) formed at an interface (<NUM>) between the meter section (<NUM>) and the transition section (<NUM>).