Combustor wall aperture body with cooling circuit

An assembly for a turbine engine is provided that includes a combustor wall, which includes an aperture body between a shell and a heat shield. The aperture body at least partially forms a cavity and an aperture that extends through the combustor wall. An inlet passage extends in the combustor wall to the cavity. An outlet passage extends in the combustor wall from the cavity to the aperture.

BACKGROUND OF THE INVENTION

1. Technical Field

This disclosure relates generally to a turbine engine and, more particularly, to a combustor for a turbine engine.

2. Background Information

A floating wall combustor for a turbine engine typically includes a bulkhead, an inner combustor wall and an outer combustor wall. The bulkhead extends radially between the inner and the outer combustor walls. Each combustor wall may include a shell and a heat shield, which heat shield forms a respective radial side of a combustion chamber. Cooling cavities extend radially between the heat shield and the shell. These cooling cavities may fluidly couple impingement apertures in the shell with effusion apertures in the heat shield.

Each combustor wall may also include a plurality of quench aperture grommets located between the shell and the heat shield. Each of the quench aperture grommets thin's a quench aperture radially through the respective combustor wall. The quench aperture grommets as well as adjacent portions of the heat shield are typically subject to relatively high temperatures during turbine engine operation, which can induce relatively high thermal stresses within the grommets and the heat shield.

There is a need in the art for an improved turbine engine combustor.

SUMMARY OF THE DISCLOSURE

According to an aspect of the invention, an assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall which includes an aperture body between a shell and a heat shield. The aperture body at least partially forms a cavity and an aperture that extends through the combustor wall. An inlet passage extends in the combustor wall to the cavity. An outlet passage extends in the combustor wall from the cavity to the aperture.

According to another aspect of the invention, a combustor wall is provided for a turbine engine. This combustor wall includes a shell, a heat shield and an aperture body axially between the shell and the heat shield. The aperture body at least partially forms a quench aperture that extends axially through the combustor wall. An inlet passage extends axially in the aperture body to an impingement cavity at least partially formed in the aperture body. An outlet passage extends radially in the aperture body from the impingement cavity to the quench aperture.

According to still another aspect of the invention, a grommet is provided for a turbine engine combustor wall through which a quench aperture extends along an axis. The grommet includes an annular aperture body that extends axially between first and second surfaces and radially between inner and outer surfaces. The inner surface at least partially forms the quench aperture. A cavity is formed at least partially within the aperture body. An inlet passage extends axially in the aperture body from an inlet orifice in the first surface to the cavity. An outlet passage extends radially in the aperture body from the cavity to an outlet orifice in the inner surface.

The aperture body may be configured with a generally c-channeled sectional geometry.

The aperture may be configured as a quench aperture.

The combustor wall may be configured to direct air through the inlet passage to impinge against a surface forming a side of the cavity. The surface may (or may not) be textured to augment convective heat transfer between the air and the combustor wall.

One or more heat transfer augmentors may be included and extend into the cavity.

The aperture may extend along an axis through the combustor wall. The inlet passage may extend axially to the cavity. The outlet passage may also or alternatively extend radially from the cavity to the aperture.

The inlet passage may be one of a plurality of inlet passages that extend in the combustor wall to the cavity. In addition or alternatively, the outlet passage may be one of a plurality of outlet passages that extend in the combustor wall from the cavity to the aperture.

The cavity may include or be configured as an annular cavity. Alternatively, the cavity may include or be configured as a semi-annular (e.g., arcuate) cavity or have various other configurations.

The aperture body may at least partially form a second cavity. A second inlet passage may extend in the combustor wall to the second cavity. A second outlet passage may extend in the combustor wall from the second cavity to the aperture.

The inlet passage may be within the aperture body. The outlet passage may also or alternatively be within the aperture body.

The aperture may be partially formed by an inner surface and a shelf surface that extends radially out to the inner surface. The outlet passage may extend to an outlet in the inner surface.

A gap may extend radially between the aperture body and the shell. A channel may extend axially into the aperture body and fluidly couple the gap with the inlet passage.

The aperture body may include a tapered flange that partially forms the aperture through the combustor wall.

The aperture body may be formed integral with the heat shield.

A second combustor wall and a combustor bulkhead may be included. The combustor wall may extend radially between the combustor wall and the second combustor wall. The combustor wall, the second combustor wall and the bulkhead may form an annular combustion chamber therebetween.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1is a side cutaway illustration of a geared turbine engine20. This turbine engine20extends along an axial centerline22between an upstream airflow inlet24and a downstream airflow exhaust26. The turbine engine20includes a fan section28, a compressor section29, a combustor section30and a turbine section31. The compressor section29includes a low pressure compressor (LPC) section29A and a high pressure compressor (HPC) section29B. The turbine section31includes a high pressure turbine (HPT) section31A and a low pressure turbine (LPT) section31B.

The engine sections28-31are arranged sequentially along the centerline22within an engine housing32. Each of the engine sections28,29A,29B,31A and31B includes a respective rotor34-38. Each of these rotors34-38includes 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 rotor34is connected to a gear train40, for example, through a fan shaft42. The gear train40and the LPC rotor35are connected to and driven by the LPT rotor38through a low speed shaft43. The HPC rotor36is connected to and driven by the HPT rotor37through a high speed shaft44. The shafts42-44are respectively rotatably supported by a plurality of bearings46; e.g., rolling element and/or thrust bearings. Each of these bearings46may be connected to the engine housing32by at least one stationary structure such as, for example, an annular support strut.

During operation, air enters the turbine engine20through the airflow inlet24, and is directed through the fan section28and into a core gas path48and a bypass gas path50. The air within the core gas path48may be referred to as “core air”. The air within the bypass gas path50may be referred to as “bypass air”. The core air is directed through the engine sections29-31, and exits the turbine engine20through the airflow exhaust26to provide forward engine thrust. Within the combustor section30, fuel is injected into a (e.g., annular) combustion chamber52and mixed with the core air. This fuel-core air mixture is ignited to power the turbine engine20. The bypass air is directed through the bypass gas path50and out of the turbine engine20through a bypass nozzle54to provide additional forward engine thrust which may account for the majority of the forward engine thrust. Alternatively, at least some of the bypass air may be directed out of the turbine engine20through a thrust reverser to provide reverse engine thrust.

FIG. 2illustrates an assembly56of the turbine engine20ofFIG. 1. The turbine engine assembly56includes a combustor58arranged within a (e.g., annular) combustor plenum60of a diffuser module62. The plenum60receives compressed core air from the HPC section29B through an inlet passage64of the diffuser module62. The plenum60provides the received core air to the combustor58as described below in further detail.

The turbine engine assembly56also includes one or more fuel injector assemblies66arranged circumferentially around the centerline22. Each of these fuel injector assemblies66includes a fuel injector68which may be mated with a swirler70. The fuel injector68injects the fuel into the combustion chamber52. The swirler70directs some of the core air from the plenum60into the combustion chamber52in a manner that facilitates mixing the core air with the injected fuel. One or more igniters (not shown) ignite the fuel-core air mixture. Quench apertures72and74(see alsoFIG. 3) in inner and/or outer walls76and78of the combustor58may direct additional core air into the combustion chamber52for combustion. Additional core air may also be directed (e.g., effused) into the combustion chamber52through one or more cooling apertures (seeFIG. 4) in the inner and the outer walls76and78.

The combustor58may be configured as an annular floating wall combustor. The combustor58ofFIG. 2, for example, includes an annular combustor bulkhead80, the tubular combustor inner wall76, and the tubular combustor outer wall78. The bulkhead80extends radially between and is connected to the inner wall76and the outer wall78. Each wall76,78extends axially along the centerline22from the bulkhead80towards the HPT section31A, thereby defining the combustion chamber52.

Each combustor component76,78and80may be a multi-walled structure that includes, for example, a heat shield (e.g.,82,84) attached to a shell (86,88). The inner and the outer walls76and78, for example, each respectively include a heat shield82,84connected to a shell86,88with one or more cooling cavities90,92(e.g., impingement cavities) between the shell86,88and the heat shield82,84. Referring toFIG. 4, each of these cooling cavities90,92may be fluidly coupled with the plenum60through one or more impingement apertures94. Each cooling cavity90,92may be fluidly coupled with the combustion chamber52through the one or more effusion apertures96. The shell86,88may be configured as a unitary full hoop body. The heat shield82,84may include one or more circumferential arrays of heat shield panels98. The present disclosure, however, is not limited to the foregoing multi-walled structure configuration.

Referring toFIGS. 2-4, the inner and/or the outer walls76and78also each include one or more (e.g., annular) aperture bodies100; e.g., grommets. Each of these aperture bodies100partially or completely forms a respective one of the quench apertures72,74through the respective combustor wall76,78along a respective axis101(seeFIG. 4). The aperture bodies100are respectively disposed circumferentially around the centerline22between the shell86,88and the heat shield82,84. Each of the aperture bodies100, for example, may be located within and extend axially (relative to the axis101) through a respective one of the cooling cavities90,92.

Referring toFIG. 4, each aperture body100may be formed integral with or attached to the heat shield82,84. Each aperture body100, for example, may be fastened, bonded (e.g., welded, brazed, adhered, etc.) and/or otherwise attached to a respective one of the heat shield panels98. Alternatively or additionally, one or more of the aperture bodies100may each be formed integral with or attached to the shell86,88.

The aperture body100may have a generally c-channeled sectional geometry. The aperture body100ofFIG. 4, for example, includes a base102integrally formed with one or more flanges104and106. The base102extends axially (relative to the axis101) between opposing surfaces108and110. The base102extends radially (relative to the axis101) between an outer surface112and an inner surface114, which may be substantially aligned with a surface116extending axially through the heat shield82,84. The outer flange104extends axially (relative to the axis101) from the base102to a distal end surface118, which may sealingly engage (e.g., contact) the shell86,88. The outer flange104extends radially (relative to the axis101) between the outer surface112and another inner surface120. The inner flange106extends axially (relative to the axis101) from the base102and a shelf surface122to a distal end surface124, and may project axially through an aperture126in the shell86,88. The inner flange106extends radially (relative to the axis101) between another outer surface128and another inner surface130. This inner surface130may be (acutely) angled relative to the axis101and thereby provide the flange106with a taper towards its distal end surface124. The shelf surface122extends radially (relative to the axis101) between the inner surfaces114and130thereby forming a shelf in the aperture body100. The surfaces114,116,122and130cooperate with one another and form the respective quench aperture72,74through the combustor wall76,78.

Each aperture body100also includes or at least partially forms at least one internal cavity132, one or more inlet passages134and one or more outlet passages136. The cavity132ofFIG. 4, for example, extends axially (relative to the axis101) between surfaces138and140. The surface138may be axially recessed into the aperture body100; e.g., the base102. The surface140may be axially recessed into the heat shield82,84. The cavity132extends radially (relative to the axis101) between an outer end142and an inner end144. The outer end142and/or the inner end144may each be formed by the aperture body100and/or the heat shield82,84. The cavity132may be annular and extend circumferentially completely around the axis101. Alternatively, the cavity132may extend laterally; e.g., circumferentially partially around the axis101. In such alternative embodiments, two or more of these cavities (e.g.,132A and132B) may be arranged about the axis101and fluidly coupled between respective passages134A, B and136A, B as shown inFIG. 5.

Referring again toFIG. 4, each inlet passage134extends radially in the combustor wall76,78and, more particularly, the base102from an inlet orifice in the surface110to the cavity132. Each inlet passage134may be located at (e.g., on, adjacent or proximate) the outer end142, and is configured to direct air from the plenum60to impinge against the surface140.

Each outlet passage136extends axially in the combustor wall76,78and, more particularly, the base102from the cavity132to an outlet orifice in the surface114and, thus, the quench aperture72,74. Each outlet passage136may be located at the surface138. In alternative embodiments, however, one or more of the outlet passages136may be formed in cooperation with the heat shield82,84or extend within the heat shield82,84.

The aperture body100may also include or at least partially form a (e.g., annular) gap146and a (e.g., an annular) channel148. The gap146extends radially (relative to the axis101) between the surfaces128and150. The channel148extends axially (relative to the axis101) into the aperture body100to the surface110. The channel148extends radially (relative to the axis101) within the aperture body100between the surfaces120and128. In this manner, the channel148fluidly couples the gap146and, thus, the plenum60to the inlet passages134. It is worth noting, the gap146and/or the channel148may be sized such that gas pressure within the channel148is substantially equal to gas pressure within the plenum60. However, the present disclosure is not limited thereto; e.g., the gas pressure within the plenum60may be higher than the gas pressure within the channel148.

During operation, core air from the plenum60is directed into the cavity132through the inlet passages134. This core air (cooling air) may impinge against the heat shield82,84and its surface140, thereby impingement cooling a region of the heat shield82,84under the aperture body100. The cooling air within the cavity132is subsequently directed through the outlet passages136into quench aperture72,74and thereafter the combustion chamber52. Within the cavity132and each passage134,136, the cooling air may also cool the heat shield82,84and/or the aperture body100through convective heat transfer. In this manner, the cavity132in cooperation with the passages134and136may cool a region of the combustor wall76,78between the aperture body100and the heat shield82,84and thereby reduce thermal stresses within this region. Furthermore, by directing the cooling air into the quench aperture72,74rather than as a film against a combustion chamber surface152of the heat shield82,84, cooling film ingestion into the quench aperture72,74may be reduced or eliminated.

In some embodiments, referring toFIG. 6, the surface140may be textured to augment convective heat transfer between the cooling air within the cavity132and the combustor wall76,78. For example, the combustor wall76,78(e.g., the heat shield82,84) may include one or more heat transfer augmentors154that project axially into the cavity132. One or more of these augmentors154may be configured to turbulate the cooling air within the cavity132. Examples of suitable augmentors154include, but are not limited to, trip strips (e.g., chevrons, linear, etc. trip strips), pins, pedestals, etc.

One or more of the aperture bodies100may each have a configuration other than those described above. For example, one or more of the aperture body100surfaces may have a circular cross-section. Alternatively, one or more of these surfaces may each have a non-circular cross-section. Examples of a non-circular cross-section include, but are not limited to, an oval cross-section, an elliptical cross-section, a pear-shaped cross-section, a teardrop cross-section, a polygonal (e.g., rectangular, triangular, etc.) cross-section, or any other symmetric or asymmetric shaped cross-section with, for example, its major axis101aligned (e.g., parallel) with the centerline22.

In some embodiments, one or more of the aperture bodies100may each be formed as a unitary body. Each aperture body100, for example, may be cast or additively manufactured as a single unit and/or machined from a single billet of material. Alternatively, one or more of the aperture bodies100may each be configured with a plurality of discrete annular body segments that are attached (e.g., bonded and/or mechanically fastened) to one another.

In some embodiments, one or more of the aperture bodies100may alternatively be configured to form other types of apertures through one or more of the combustor walls82,84. For example, at least one of the aperture bodies100may define an aperture that receives an igniter. In another example, at least one of the aperture bodies100may define an aperture that may receive a borescope during combustor58maintenance and/or inspection.

The turbine engine assembly56may be included in various turbine engines other than the one described above. The turbine engine assembly56, 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 turbine engine assembly56may be included in a turbine engine configured without a gear train. The turbine engine assembly56may be included in a geared or non-geared turbine engine configured with a single spool, with two spools (e.g., seeFIG. 1), or with more than two spools. The turbine engine may be configured as a turbofan engine, a turbojet engine, a propfan engine, or any other type of turbine engine. The present invention therefore is not limited to any particular types or configurations of turbine engines.