Patent Description:
A turbine engine typically includes a cooling system for cooling one or more internal components of the turbine engine. For example, it is known to air cool a turbine vane with compressed air. However, bleeding air from a compressor of the turbine engine decreases efficiency of the turbine engine, particularly where the cooling air is routed through a tortuous path within an engine casing. <CIT> and <CIT> disclose arrangements with cases and air conduits of the prior art.

There is a need in the art therefore for improved systems for providing cooling air to internal components of a turbine engine.

In an aspect of the present invention, an assembly is provided for a turbine engine according to claim <NUM>.

The following optional features may be applied to any of the above aspects of the invention.

More than fifty percent of the conduit centerline may follow a curved trajectory.

The turbine engine assembly may also include a compressor section and a turbine vane. The compressor section is at least partially housed within the case structure. The turbine vane is configured with one or more internal passages. The air conduit is fluidly coupled with and between the compressor section and the one or more internal passages.

The non-straight trajectory may be a continuously curved trajectory.

An entirety of the conduit centerline may follow the non-straight trajectory.

The conduit centerline may be angularly offset from the case structure at the conduit first end by a first included angle. The conduit centerline may be angularly offset from the case structure at the conduit second end by a second included angle that is different than the first included angle.

The first location may be displaced from the second location axially along the axis.

The first location may be displaced from the second location circumferentially about the axis.

At least a portion of the air conduit may have a polygonal cross-sectional geometry.

At least a portion of the air conduit may have an elongated cross-sectional geometry.

The turbine engine assembly may also include an air source and an air cooled component within the case structure. The air conduit may be configured to receive air from the air source and direct the received air to the air cooled component.

The air source may be configured as or otherwise include a compressor section of the turbine engine. In addition or alternatively, the air cooled component may be configured as or otherwise include a turbine vane.

The turbine engine assembly may also include a stator vane with one or more internal passages. The air conduit may be fluidly coupled with the one or more internal passages.

The turbine engine assembly may also include a second air conduit within the case structure. The second air conduit may extend radially across a flowpath (e.g. a downstream portion of a flowpath) of the turbine engine. The second air conduit may be fluidly coupled with and downstream of the air conduit.

The air conduit may be fluidly coupled with a bleed orifice in the case structure at the conduit first end.

The turbine engine assembly may also include a scoop connected to the case structure. The scoop may project into a flowpath (e.g. an upsteam portion of the flowpath) of the turbine engine. The air conduit may be fluidly coupled with and downstream of the scoop.

The conduit first end may be an upstream end of the air conduit. The conduit second end may be a downstream end of the air conduit. A maximum displacement between the case structure and the air conduit may be longitudinally along the conduit centerline closer to the conduit second end than the conduit first end.

<FIG> is a schematic illustration of a gas turbine engine <NUM>. This turbine engine <NUM> includes a compressor section <NUM>, a combustor section <NUM> and a turbine section <NUM>. The turbine engine <NUM> also includes a turbine engine case structure <NUM> and an air cooling system <NUM>.

The case structure <NUM> is configured to at least partially or completely house and/or support any one or more or all of the turbine engine sections <NUM>-<NUM>. Referring to <FIG>, the case structure <NUM> has a centerline axis <NUM>, a case first end <NUM> (e.g., an upstream and/or forward end) and a case second end <NUM> (e.g., a downstream and/or aft end). The case structure <NUM> of <FIG> extends axially along its centerline axis <NUM> between and to the case first end <NUM> and the case second end <NUM>. Referring to <FIG>, the case structure <NUM> extends circumferentially about the centerline axis <NUM>. The case structure <NUM> of <FIG>, for example, extends completely around the centerline axis <NUM> thereby providing the case structure <NUM> with a full-hoop, tubular body.

The cooling system <NUM> of <FIG> is configured to cool at least one air cooled component <NUM> of the turbine engine <NUM>. The air cooled component <NUM> of <FIG> is arranged radially within an (e.g., tubular) outer casing wall <NUM> of the case structure <NUM>. For ease of description, the air cooled component <NUM> may be described below as a stator vane array <NUM>; e.g., a turbine inlet nozzle, a combustor outlet nozzle, etc. The present disclosure, however, is not limited to such an exemplary air cooled component. For example, in other embodiments, the cooling system <NUM> may also or alternatively be configured for cooling a turbine engine wall (e.g., a combustor wall, a liner wall, a shroud, a blade outer air seal (BOAS), etc.), a turbine engine rotor blade (e.g., a turbine blade) or any other component within the turbine engine <NUM> which may utilize air cooling.

Referring to <FIG>, the cooling system <NUM> includes at least one (e.g., exterior) air conduit <NUM>; e.g., a pipe, a duct, etc. The air conduit <NUM> has a conduit centerline <NUM>, a conduit first end <NUM> (e.g., an upstream end) and a conduit second end <NUM> (e.g., a downstream end). The air conduit <NUM> extends longitudinally along its conduit centerline <NUM> between and to the conduit first end <NUM> and the conduit second end <NUM>. The conduit first end <NUM> is connected to the case structure <NUM> and its outer casing wall <NUM> at a first location. The conduit second end <NUM> is connected to the case structure <NUM> and its outer casing wall <NUM> at a second location. Referring to <FIG>, the second location may be axially displaced from the first location along the centerline axis <NUM> by an axial distance <NUM>. The second location may also or alternatively be circumferentially displaced from the first location about the centerline axis <NUM> by a circumferential distance <NUM>. This circumferential distance <NUM> may be different (e.g., greater or less) than or equal to the axial distance <NUM>.

The air flowing within the turbine engine <NUM> may have swirl. More particularly, in addition to flowing axially and/or radially within the turbine engine <NUM> (e.g., along a flowpath), the air may also flow circumferentially (e.g., clockwise or counter-clockwise) about the centerline axis <NUM>. In order to preserve circumferential momentum, the second location of the conduit second end <NUM> may be positioned circumferentially relative to the first location of the conduit first end <NUM> such that the air conduit <NUM> and its conduit centerline <NUM> are substantially (e.g., +/- <NUM> degrees) or exactly parallel with the air bled from the compressor section <NUM>; the air source <NUM>. The present disclosure, however, is not limited to such an exemplary configuration.

The air conduit <NUM> may be arranged radially outboard of the outer casing wall <NUM>. The air conduit <NUM> of <FIG>, for example, is radially displaced from the case structure <NUM> and its outer casing wall <NUM> longitudinally between the conduit first end <NUM> and the conduit second end <NUM>. In particular, at least an intermediate portion or an entirety of the air conduit <NUM> (longitudinally along its centerline <NUM> between the conduit ends <NUM> and <NUM>) is spatially separated from the case structure <NUM> and its outer casing wall <NUM> by a (e.g., air) gap <NUM>. Thus, longitudinally along the conduit centerline <NUM> between the conduit ends <NUM> and <NUM>, the air conduit <NUM> may be completely self-supported. Of course, in other embodiments, the air conduit <NUM> may be structurally tied to the case structure <NUM> and its outer casing wall <NUM> by one or more supports <NUM> (e.g., stanchions, struts, etc.) as shown, for example, in <FIG>.

Referring to <FIG>, the air conduit <NUM> is configured to receive air (e.g., compressed air) from an air source <NUM> and then direct that received air to the stator vane array <NUM>; the air cooled component <NUM>. For ease of description, the air source <NUM> may be described below as the compressor section <NUM> of the turbine engine <NUM>. The present disclosure, however, is not limited to such an exemplary air source. For example, in other embodiments, the air source <NUM> may alternatively be a diffuser passage <NUM> from the compressor section <NUM> to the combustor section <NUM>.

The air conduit <NUM> is configured to preserve of momentum of the air received (e.g., bled) from the compressor section <NUM> and directed towards the stator vane array <NUM>. The air conduit <NUM> of <FIG>, for example, is configured to soar over an exterior of the case structure <NUM> and its outer casing wall <NUM> and then dive to the case structure <NUM> and its outer casing wall <NUM> towards the stator vane array <NUM>. With such a configuration, the cooling system <NUM> can utilize (e.g., bleed) less air for cooling the stator vane array <NUM> and, thus, increase efficiency of the turbine engine <NUM>.

At least a major portion (e.g., more than fifty percent (<NUM>%)) of the air conduit <NUM> and its centerline <NUM> follows a non-straight trajectory. For example, at least sixty percent (<NUM>%), seventy percent (<NUM>%), eighty percent (<NUM>%) or more (e.g., an entirety) of the air conduit <NUM> and its centerline <NUM> may follow a continuously curved trajectory, a splined trajectory, an arcuate trajectory or any other non-straight trajectory from the conduit first end <NUM> and to the conduit second end <NUM>. At least a portion or an entirety of the non-straight trajectory may have a variable radius. Thus, a maximum (e.g., radial) displacement <NUM> between (a) the case structure <NUM> and its outer casing wall <NUM> and (b) the air conduit <NUM> may be, longitudinally along the conduit centerline <NUM>, closer to the conduit second end <NUM> than the conduit first end <NUM>. For example, a location of the maximum displacement <NUM> may be in a last / downstream-most one-half (<NUM>/<NUM>), two-fifths (<NUM>/<NUM>) or one-third (<NUM>/<NUM>) of the air conduit <NUM>. With such a configuration, the air conduit <NUM> may dive to the conduit second end <NUM>.

The air conduit <NUM> is angularly offset from the case structure <NUM> and its outer casing wall <NUM> by a (e.g., acute) first included angle <NUM> at the conduit first end <NUM>. The air conduit <NUM> is angularly offset from the case structure <NUM> and its outer casing wall <NUM> by a (e.g., acute) second included angle <NUM> at the conduit second end <NUM>. The second included angle <NUM> of <FIG> is different (e.g., greater) than the first included angle <NUM>.

Referring to <FIG>, at least a portion or an entirety of the air conduit <NUM> may have a (e.g., interior and/or exterior) non-circular cross-sectional geometry when viewed, for example, in a plane perpendicular to the conduit centerline <NUM>. Referring to <FIG>, the non-circular cross-sectional geometry may have an elongated shape with a major axis <NUM> and a minor axis <NUM>. For example, referring to <FIG>, the non-circular cross-sectional geometry may have an oval shape, an elliptical shape or a race-track shape. In another example, referring to <FIG>, the non-circular cross-sectional geometry may have a teardrop shape. Referring to <FIG>, the non-circular cross-sectional geometry may also or alternatively have polygonal shape. The non-circular cross-sectional geometry of <FIG>, for example, may have a diamond shape or square shape. The present disclosure, however, is not limited to the foregoing exemplary air conduit cross-sectional geometries.

While the present disclosure is not limited to any particular air conduit cross-sectional geometry, the air conduit cross-sectional geometries described above may be particularly useful where the air conduit <NUM> is manufactured via, for example, additive manufacturing. The above described air conduit cross-sectional geometries, for example, may facilitate forming the air conduit <NUM> without any internal support structures (e.g., support structures within a bore of the air conduit <NUM>) and/or reduce or minimize inter-layer overhangs during additive manufacture. During additive manufacture, the air conduit <NUM> may be arranged such that, for example, the major axis <NUM> or a diagonal <NUM>' of the air conduit cross-sectional geometry is substantially (e.g., +/- <NUM> degrees) or exactly parallel with a layer-by-layer build direction <NUM>.

Referring to <FIG>, the air conduit <NUM> and its first end <NUM> may be fluidly coupled with a flowpath <NUM> (e.g., a core gas path) within the compressor section <NUM> through a bleed aperture <NUM>; e.g., orifice, through-hole, etc. The bleed aperture <NUM> of <FIG> is disposed in and extends through the case structure <NUM> and its outer casing wall <NUM>. Alternatively, referring to <FIG>, the air conduit <NUM> and its first end <NUM> may be fluidly coupled with the flowpath <NUM> through an air scoop <NUM>. The air scoop <NUM> of <FIG> is connected to the case structure <NUM> and its outer casing wall <NUM> and projects into the flowpath <NUM>.

Referring to <FIG>, the air conduit <NUM> and its second end <NUM> may be fluidly coupled with at least one internal passage <NUM> of the stator vane array <NUM> (e.g., directly) through an aperture <NUM> in the case structure <NUM> / the outer casing wall <NUM>. Alternatively, referring to <FIG>, the air conduit <NUM> and its second end <NUM> may be fluidly coupled with the at least one internal passage <NUM> of the stator vane array <NUM> (e.g., indirectly) through at least one intermediate structure <NUM> and/or another portion of the case structure <NUM> (or another structure). For example, the air conduit <NUM> may be fluidly coupled, in serial, with the aperture <NUM> in the outer casing wall <NUM>, at least one internal passage <NUM> of the intermediate structure <NUM>, an aperture <NUM> in an inner casing wall <NUM> of the case structure <NUM>, and the at least one internal passage <NUM> of the stator vane array <NUM>. The intermediate structure <NUM> may be an internal air conduit exposed to the flowpath <NUM>. This internal air conduit may have a similar geometry to the external air conduit <NUM>. Alternatively, the internal air conduit may have a cross-sectional geometry with an airfoil shape or another aerodynamic shape. The internal air conduit may extend radially across (e.g., a diffuser portion of) the flowpath <NUM> between and to the casing walls <NUM> and <NUM>. Alternatively, the intermediate structure <NUM> may be another stator vane array (e.g., a diffuser vane array) or a stator vane thereof with one or more internal passages (e.g., <NUM>, 80A, 80B, 80C, <NUM>).

Referring to <FIG>, the stator vane array <NUM> includes a plurality of stator vanes <NUM>; e.g., turbine vanes. These stator vanes <NUM> are arranged circumferentially about the centerline axis <NUM> in an annular array. At least one (or only one) of the stator vanes <NUM> is hollow and fluidly coupled with / receives the cooling air from the air conduit <NUM>.

Referring to <FIG>, the at least one stator vane <NUM> may be configured with a single internal passage <NUM> fluidly coupled with and downstream of the air conduit <NUM> (see <FIG>). However, referring to <FIG>, the at least one stator vane <NUM> may be configured with a plurality of (e.g., parallel) internal passages 80A, 80B and 80C (generally referred to as "<NUM>") (e.g., branches, capillaries, etc.) fluidly coupled with and downstream of the air conduit <NUM> (see <FIG>).

The internal passage(s) <NUM> in the at least one stator vane <NUM> may be configured to provide the cooling air to another downstream volume <NUM> (see <FIG>); e.g., a cavity or passage. Each internal passage <NUM>, for example, may extend radially through (or out of) the respective stator vane <NUM>. The present disclosure, however, is not limited to the above exemplary internal passage configurations.

In some embodiments, referring to <FIG> and <FIG>, the turbine engine <NUM> may include a single air conduit <NUM> external to the case structure <NUM> and its outer casing wall <NUM>. This single air conduit <NUM> may service a single one of the stator vanes <NUM> (e.g., see <FIG>), some of the stator vanes <NUM> (see <FIG>) or each of the stator vanes <NUM>. Alternatively, each stator vane <NUM>, or a subset (e.g., every other one) of the stator vanes <NUM>, may be configured with its own respective air conduit <NUM>. For example, referring to <FIG> and <FIG>, the cooling system <NUM> includes a plurality of the air conduits <NUM> external to the case structure <NUM>. Each of these air conduits <NUM> is respectively fluidly coupled with a respective one of the stator vanes <NUM> in the stator vane array <NUM>. In the embodiment of <FIG>, a subset of the stator vanes <NUM> in the stator vane array <NUM> are cooled by air from the respective air conduits <NUM>. In the embodiment of <FIG>, each of the stator vanes <NUM> in the stator vane array <NUM> is cooled by air from a respective one of the air conduits <NUM>. Of course, in still other embodiments, the turbine engine <NUM> may include a plurality of the air conduits <NUM>, where each air conduit <NUM> may service multiple stator vanes <NUM> (e.g., see optional dashed lines in <FIG>). The present disclosure, of course, is not limited to the foregoing exemplary pairings / configurations of air conduits <NUM> and stator vanes <NUM>.

Referring to <FIG>, the case structure <NUM> may include a plurality of walls. The case structure <NUM> of <FIG>, for example, includes a compressor wall <NUM> (e.g., a forward portion of the outer casing wall <NUM>), a diffuser wall <NUM> (e.g., an aft portion of the outer casing wall <NUM>), an outer combustor wall <NUM> of a (e.g., annular) combustor <NUM>, an inner combustor wall <NUM> of the combustor <NUM>, a bulkhead wall <NUM> of the combustor <NUM>, an outer turbine wall <NUM> and an inner turbine wall <NUM>. One or more or each of these case walls <NUM>-<NUM> may be generally tubular or generally annular. Each of the case walls <NUM>-<NUM>, <NUM> and <NUM> of <FIG>, for example, is tubular, and the bulkhead wall <NUM> is annular.

The compressor wall <NUM> extends axially along the centerline axis <NUM> between and is connected to an inlet section <NUM> of the turbine engine <NUM> and the diffuser wall <NUM>. The compressor wall <NUM> of <FIG> circumscribes, axially overlaps and thereby houses a rotor <NUM> of the compressor section <NUM>.

The diffuser wall <NUM> extends axially along the centerline axis <NUM> between and is connected to the compressor wall <NUM> and an aft end portion of the inner turbine wall <NUM>. The diffuser wall <NUM> is spaced / displaced radially outboard from and axially overlaps the combustor <NUM>. The diffuser wall <NUM> of <FIG> thereby forms an outer peripheral boundary of a diffuser plenum <NUM> that surrounds the combustor <NUM>.

The outer combustor wall <NUM> extends axially along the centerline axis <NUM> between and may be connected to the bulkhead wall <NUM> and an outer platform <NUM> of the stator vane array <NUM>. The inner combustor wall <NUM> is circumscribed and axially overlapped by the outer combustor wall <NUM>. The inner combustor wall <NUM> extends axially along the centerline axis <NUM> between and may be connected to the bulkhead wall <NUM> and an inner platform <NUM> of the stator vane array <NUM>. The bulkhead wall <NUM> extends radially between and is connected to aft end portions of the outer combustor wall <NUM> and the inner combustor wall <NUM>. The case walls <NUM>-<NUM> may thereby collectively form peripheral boundaries of a (e.g., annular) combustion chamber <NUM> therebetween.

The outer turbine wall <NUM> may be connected to the stator vane array platform <NUM>. The outer turbine wall <NUM> projects axially out from the stator vane array platform <NUM> and extends axially towards / to an aft, downstream end of an inner platform <NUM> of the compressor rotor <NUM>. This outer turbine wall <NUM> is circumscribed and axially overlapped by the diffuser wall <NUM>. The outer turbine wall <NUM> of <FIG> may thereby form an inner peripheral boundary of the flowpath <NUM> within a diffuser <NUM> of the turbine engine <NUM>, and may form an outer peripheral boundary of the flowpath <NUM> within a (e.g., upstream) portion of the turbine section <NUM>. The outer turbine wall <NUM> of <FIG> also circumscribes, axially overlaps and thereby houses a (e.g., upstream) portion of a rotor <NUM> of the turbine section <NUM>.

The inner turbine wall <NUM> may be connected to the stator vane array platform <NUM>. An upstream portion of the inner turbine wall <NUM> projects axially (in an aft-to-forward direction) out from the stator vane array platform <NUM> to a turning portion of the inner turbine wall <NUM>. A downstream portion of the inner turbine wall <NUM> projects axially (in a forward-to-aft direction) away from the inner turbine wall turning portion to an outlet of the turbine section <NUM> at the case second end <NUM>. The inner turbine wall <NUM> is circumscribed and axially overlapped by the combustor <NUM>. The inner turbine wall <NUM> is also spaced / displaced radially inboard from the combustor <NUM>. The inner turbine wall <NUM> of <FIG> thereby forms an inner peripheral boundary of the diffuser plenum <NUM> that surrounds the combustor <NUM>. The inner turbine wall <NUM> forms an outer peripheral boundary of the core flowpath <NUM> within a (e.g., downstream) portion of the turbine section <NUM>. The inner turbine wall <NUM> of <FIG> also circumscribes, axially overlaps and thereby houses a (e.g., downstream) portion of the turbine rotor <NUM>.

The case structure <NUM> may also include one or more internal support structures with one or more support members. Examples of support members include, but are not limited to, struts, structural guide vanes, bearing supports, bearing compartment walls, etc. The case structure <NUM> of <FIG>, for example, includes a forward support structure <NUM>, an aft support structure <NUM>, an inlet nozzle <NUM> and the stator vane array <NUM>. The forward support structure <NUM> may be configured to support a shaft bearing <NUM>. The aft support structure <NUM> may be configured to support another shaft bearing <NUM>. The inlet nozzle <NUM> may be configured to condition core air entering the compressor section <NUM>. The inlet nozzle <NUM>, for example, may include one or more guide vanes <NUM> which impart swirl to the core air. The stator vane array <NUM> may similarly be configured to condition the combustion products exiting the combustor section <NUM>. The stator vanes <NUM>, for example, may import swirl to the combustion products, where these stator vanes <NUM> are connected to and extend radially between the stator vane array inner and outer platforms <NUM> and <NUM>. The case structure <NUM>, of course, may also or alternative include various other static / stationary gas turbine engine components.

With the configuration of <FIG>, cooling air provided to the stator vane(s) <NUM> may also be provided to cool the stator vane array inner platform <NUM> and/or a forward / downstream portion of the inner combustor wall <NUM> before flowing into the combustion chamber <NUM>.

Some or all stationary components (e.g., <NUM>, <NUM> and <NUM>) of the turbine engine <NUM> is formed (e.g., additively manufactured) together as a single monolithic body. The term monolithic describes an apparatus which is formed as a single unitary body. According to the invention, the components (e.g., <NUM>, <NUM>, <NUM> and/or <NUM>) in <FIG> or the components (e.g., <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM> and/or <NUM>) in <FIG>, for example, are collectively additively manufactured, cast, machined and/or otherwise formed together as an integral, unitary body. Thus, the cooling system components (e.g., the air conduits <NUM> and <NUM>) are configured as part of the case structure <NUM>. By contrast, a non-monolithic body includes parts that are discretely formed from one another, where those parts are subsequently mechanically fastened and/or otherwise attached to one another.

The cooling system <NUM> and its air conduit(s) <NUM> may be included in various turbine engines. The cooling system <NUM> and its air conduit(s) <NUM>, for example, may be included in a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the cooling system <NUM> and its air conduit(s) <NUM> may be included in a turbine engine configured without a gear train. The cooling system <NUM> and its air conduit(s) <NUM> may be included in a geared or non-geared turbine engine configured with a single spool (see <FIG>), with two spools, or with more than two spools. The turbine engine may be configured as a turbofan engine, a turbojet engine, a propfan engine, a pusher fan engine or any other type of turbine engine. The present disclosure therefore is not limited to any particular types or configurations of turbine engines.

Claim 1:
An assembly for a turbine engine, comprising:
a case structure (<NUM>) extending circumferentially about and axially along an axis (<NUM>); and
an air conduit (<NUM>) having a conduit centerline (<NUM>), a conduit first end (<NUM>) and a conduit second end (<NUM>), the air conduit extending longitudinally along the conduit centerline (<NUM>) between the conduit first end (<NUM>) and the conduit second end (<NUM>), the conduit first end (<NUM>) connected to the case structure (<NUM>) at a first location, the conduit second end (<NUM>) connected to the case structure (<NUM>) at a second location, the air conduit (<NUM>) displaced from the case structure (<NUM>) longitudinally between the conduit first end (<NUM>) and the conduit second end (<NUM>), and at least a majority of the conduit centerline (<NUM>) following a non-straight trajectory;
characterised in that
the case structure (<NUM>) and the air conduit (<NUM>) are formed together as a monolithic body.