Patent Description:
Rotational equipment such as a gas turbine engine may include a fluid delivery system for delivering lubricant and/or coolant to one or more components within the gas turbine engine. As engine designs continue to progress, space available within the gas turbine engine continues to decrease making it more and more difficult to utilize traditional fluid delivery system components. There is a need in the art therefore for an improved fluid delivery system.

<CIT> discloses features of the preamble of claim <NUM>. Similar assemblies are also known from <CIT>, <CIT> and <CIT>.

According to an aspect of the present invention, an assembly is provided for rotational equipment as claimed in claim <NUM>. Various embodiments of the invention are provided by the dependent claims.

<FIG> is a partial side sectional illustration of an assembly <NUM> for a piece of rotational equipment. The piece of rotational equipment may be configured as a gas turbine engine for an aircraft propulsion system such as, but not limited to, a geared or direct-drive turbofan gas turbine engine. However, the assembly <NUM> of the present disclosure is not limited to such an aircraft application nor a gas turbine engine application. The assembly <NUM>, for example, may alternatively be configured with rotational equipment such as an industrial gas turbine engine, a wind turbine, a water turbine or any other apparatus which includes a seal assembly for sealing a gap between a rotating component and a static / fixed component.

The assembly <NUM> of <FIG> includes a static structure <NUM>, a rotating structure <NUM> and at least one bearing <NUM> for rotatably supporting the rotating structure <NUM> relative to the static structure <NUM>. The assembly <NUM> of <FIG> also includes a seal assembly <NUM>.

The static structure <NUM> is configured as a stationary part of the rotational equipment. The static structure <NUM> of <FIG>, for example, is configured to at least partially form an internal bearing compartment <NUM> for housing at least the bearing <NUM>. This static structure <NUM> includes a bearing support <NUM> such as, but not limited to, a strut. The static structure <NUM> also includes a seal assembly support <NUM>; e.g., an annular wall. The seal assembly support <NUM> of <FIG> is configured with an internal static structure fluid passage <NUM> which extends within the static structure <NUM> and, more particularly, the seal assembly support <NUM>. The static structure fluid passage <NUM> is configured to receive fluid (e.g., lubricant, coolant, etc.) from a fluid source <NUM> such as, but not limited to, a reservoir, pump, etc..

The rotating structure <NUM> is rotatable about an axial centerline <NUM>, which centerline <NUM> may be an axial centerline and/or a rotational axis of the rotational equipment. The rotating structure <NUM> of <FIG> is configured as a tubular shaft. However, in other embodiments, the rotating structure <NUM> may be configured as another component (e.g., a sleeve) mounted to and rotatable with a shaft of the rotational equipment, or any other rotor within the rotational equipment. The rotating structure <NUM> of <FIG> extends axially along the axial centerline <NUM> through (or partially into or within) the static structure <NUM>. The static structure <NUM> of <FIG> thereby extends circumferentially about (e.g., completely around) the axial centerline <NUM> and the rotating structure <NUM>.

The bearing <NUM> may be configured as a roller element bearing. The bearing <NUM> of <FIG>, for example, includes an annular outer race <NUM>, an annular inner race <NUM> and a plurality of bearing elements <NUM>; e.g., cylindrical or spherical elements. The outer race <NUM> circumscribes the inner race <NUM> and the bearing elements <NUM>. The outer race <NUM> is mounted to the static structure <NUM> and, more particularly, the bearing support <NUM>. The inner race <NUM> circumscribes and is mounted to the rotating structure <NUM>. The bearing elements <NUM> are arranged in an annular array about the axial centerline <NUM>, which array is radially between and engaged with the outer race <NUM> and the inner race <NUM>. The present disclosure, however, is not limited to the foregoing exemplary bearing configuration. For example, in other embodiments, the bearing <NUM> may alternatively be configured as a journal bearing or any other type of bearing utilized in the rotational equipment.

The seal assembly <NUM> is configured to seal an annular gap between a rotating assembly <NUM> and the static structure <NUM>, which rotating assembly <NUM> includes at least the rotating structure <NUM>. The seal assembly <NUM> of <FIG>, for example, is configured to seal the gap which extends (e.g., radially and/or axially) between the static structure <NUM> and the rotating structure <NUM>. Of course, in other embodiments, the seal assembly <NUM> may seal a gap extending between the static structure <NUM> and another rotating component mounted to and/or rotatable with the rotating structure <NUM>.

The seal assembly <NUM> of <FIG> includes an annular seal land <NUM> and an annular seal element <NUM>; e.g., a carbon seal element. The seal assembly <NUM> of <FIG> also includes one or more guide rails <NUM> and a seal support assembly <NUM>.

The seal land <NUM> is configured with a full hoop body that extends circumferentially about the axial centerline <NUM>. The seal land <NUM> extends axially along the axial centerline <NUM> between an axial first end <NUM> and an axial second end <NUM>. The seal land <NUM> extends radially between a radial inner side <NUM> and a radial outer side <NUM>.

The seal land <NUM> includes an annular, radially extending seal land surface <NUM> located at (e.g., on, adjacent or proximate) the axial second end <NUM>. This seal land surface <NUM> may be an uninterrupted surface. The seal land surface <NUM>, for example, may be a flat planar surface configured without circumferential and/or radial interruptions such as, but not limited to, channels, slots and apertures. Of course, in other embodiments, the seal land surface <NUM> may be circumferentially and/or radially interrupted by one or more channels, slots, apertures and/or other types of surface interruptions.

Referring to <FIG>, the seal element <NUM> is configured with a full hoop body that extends circumferentially about the axial centerline <NUM>. This full hoop body may be a single unitary body; e.g., a monolithic body. Alternatively, the full hoop body may be a segmented body; e.g., the seal element <NUM> may be configured from an array of arcuate seal element segments. The seal element <NUM> extends axially along the axial centerline <NUM> between an axial first end <NUM> and an axial second end <NUM>. The seal element <NUM> extends radially between a radial inner side <NUM> and a radial outer side <NUM>.

The seal element <NUM> includes an annular, radially extending seal element surface <NUM> located at (e.g., on, adjacent or proximate) the axial first end <NUM>. This seal element surface <NUM> may be an uninterrupted surface. The seal element surface <NUM>, for example, may be a flat planar surface configured without circumferential and/or radial interruptions such as, but not limited to, channels, slots and apertures. Of course, in other embodiments, the seal element surface <NUM> may be circumferentially and/or radially interrupted by one or more channels, slots, apertures and/or other types of surface interruptions.

Referring to <FIG>, the guide rails <NUM> are arranged circumferentially about the axial centerline <NUM> in an annular array. Referring to <FIG>, each of the guide rails <NUM> may be configured as or otherwise include a guide pin. For example, each guide rail <NUM> of <FIG> may have, but is not limited to, a generally cylindrical body <NUM> that extends axially between an axial first end <NUM> and an axial second end <NUM>. A generally annular flange <NUM> may project out from and circumscribes the body <NUM>. This flange <NUM> may be configured with a polygonal (e.g., hexagonal) peripheral cross-sectional geometry adapted for mating with an installation tool such as, but not limited to, a wrench or a socket. An axial first portion <NUM> of the body <NUM>, axially between the axial first end <NUM> and the flange <NUM>, may be configured with threads; e.g., the portion is a threaded portion. An axial second portion <NUM> of the body <NUM>, axially between the axial second end <NUM> and the flange <NUM>, may be configured with a smooth cylindrical surface.

Referring to <FIG>, at least one, some or all of the guide rails <NUM> is each respectively configured with an internal guide rail fluid passage <NUM> (e.g., a pin fluid passage) and a fluid delivery nozzle <NUM>. The guide rail fluid passage <NUM> includes / is formed by a (e.g., single) passageway through the guide rail <NUM>. This passageway includes / is formed by a bore. This bore extends along a centerline <NUM> of the guide rail fluid passage <NUM> partially into the guide rail <NUM> from the axial first end <NUM> to the nozzle <NUM>.

The nozzle <NUM> is disposed at the axial second end <NUM>. The nozzle <NUM> is configured with an internal nozzle fluid passage <NUM>. The nozzle fluid passage <NUM> includes / is formed by a (e.g., single) passageway through the nozzle <NUM>. This passageway includes / is formed by a bore. This bore extends along a nozzle orifice centerline <NUM> from the guide rail fluid passage <NUM> to an orifice <NUM> of the nozzle <NUM>. The nozzle fluid passage <NUM> thereby extends between and fluidly couples the guide rail fluid passage <NUM> to the nozzle orifice <NUM>.

The nozzle orifice centerline <NUM> is angularly offset from the guide rail fluid passage centerline <NUM> by an included angle <NUM>; e.g., an obtuse angle or an acute angle. The centerlines <NUM> and <NUM>, for example, may be angularly offset by between one hundred and ten degrees (<NUM>°) and one hundred and sixty degrees (<NUM>°). The present disclosure, however, is not limited to such exemplary angles. For example, in other embodiments, the angle <NUM> may be less than one hundred and ten degrees (<NUM>°) or greater than one hundred and sixty degrees (<NUM>°). Note, in some embodiments, the respective guide rail <NUM> may be configured with more than one nozzle fluid passage <NUM> and/or nozzle orifice <NUM>.

Referring to <FIG>, the seal support assembly <NUM> is configured to translate axially along the guide rails <NUM>. The seal support assembly <NUM> is also configured to support the seal element <NUM>. The seal support assembly <NUM> of <FIG>, for example, is configured as or otherwise includes a seal carrier <NUM>.

Referring to <FIG>, the seal carrier <NUM> is configured with a full hoop body that extends circumferentially about the axial centerline <NUM>; see also <FIG>. The seal carrier <NUM> extends axially along the axial centerline <NUM> between an axial first end <NUM> and an axial second end <NUM>. The seal carrier <NUM> extends radially, relative to the axial centerline <NUM>, between a radial inner side <NUM> and a radial outer side <NUM>.

The seal carrier <NUM> of <FIG> includes a tubular carrier base <NUM> and one or more carrier flanges <NUM>; see also <FIG>. The base <NUM> is configured with an annular recess / notch <NUM>. This recess <NUM> extends axially partially into the base <NUM> from the axial first end <NUM> to an (e.g., annular) axial end surface <NUM>. The recess <NUM> extends radially partially into the base <NUM> from the radial inner side <NUM> to a (e.g., tubular) radial end surface <NUM>. The recess <NUM> forms a receptacle for the seal element <NUM> as described below in further detail.

Referring to <FIG>, the flanges <NUM> are arranged circumferentially about the base <NUM>. Each flange <NUM> includes a slot <NUM>.

Referring to <FIG>, the seal land <NUM> is arranged with the rotating structure <NUM> in such a manner so as to be rotatable with the rotating structure <NUM> about the axial centerline <NUM>. The seal land <NUM> of <FIG>, for example, circumscribes and is fixedly mounted to the rotating structure <NUM>; e.g., clamped between the inner race <NUM> and a shoulder on the rotating structure <NUM>.

The guide rails <NUM> are fixedly mounted to the static structure <NUM>. For example, the threaded portion <NUM> of each guide rail <NUM> may be screwed into a corresponding tapped hole <NUM> in the static structure <NUM>. Each guide rail <NUM> is thereby connected to the static structure <NUM> by a threaded interface. However, in other embodiments, each guide rail <NUM> may also or alternatively be connected to the static structure <NUM> through another type of interface connection; e.g., staking, riveting, press fitting, bolting, etc..

The seal element <NUM> is seated in the receptacle of the seal carrier <NUM>. A split ring <NUM> and/or another device secures the seal element <NUM> within the receptacle such that the seal element <NUM> is fixedly mounted to the seal carrier <NUM>. Of course, the seal element <NUM> may also or alternatively be mounted to the seal carrier <NUM> using other fastening and/or bonding techniques.

The seal carrier <NUM> is mated with the guide rails <NUM>. In particular, each of the guide rails <NUM> projects through a respective flange slot <NUM>; see also <FIG>.

One or more spring elements <NUM> may be arranged between the static structure <NUM> and the seal carrier <NUM>. These spring elements <NUM> are configured to bias the seal carrier <NUM> and, thus, the seal element <NUM> away from the static structure <NUM> and towards the seal land <NUM>. In particular, the spring elements <NUM> cause the surfaces <NUM> and <NUM> to axially sealingly engage (e.g., contact) one another.

During operation, the seal element <NUM> sealingly engages the seal land <NUM>. A combination of at least the seal element <NUM> and the seal support assembly <NUM> seal a gap between the seal land <NUM> and the static structure <NUM> and thereby fluidly divide (e.g., separate, isolate) the bearing compartment <NUM> from another plenum <NUM>.

In addition, in order to cool and/or provide lubrication to the bearing <NUM> (e.g., interfaces between the bearing elements <NUM> and the races <NUM> and <NUM>), each static structure fluid passage <NUM> supplies fluid (e.g., lubricant, coolant, oil, etc.) to a respective one of the guide rail fluid passages <NUM>. Each guide rail fluid passage <NUM> supplies this received fluid to a respective one of the nozzles <NUM>. Each nozzle <NUM> is configured to direct the received fluid out of its nozzle orifice <NUM> along the nozzle orifice centerline <NUM> towards the bearing <NUM>. The fluid injected / discharged by the nozzle <NUM> may travel along a trajectory <NUM> that extends to (e.g., is coincident with) the bearing <NUM> and one or more of its components <NUM>-<NUM> (e.g., the inner race <NUM>).

In some embodiments, the assembly <NUM> may also include one or more secondary seals <NUM>. The assembly <NUM> of <FIG>, for example, includes an annular secondary seal element <NUM> axially between the seal element <NUM> and the seal carrier <NUM>. This secondary seal element <NUM> is configured to separate cooling fluids from boundary fluids.

<FIG> is a side cutaway illustration of a geared turbine engine <NUM> with which the assembly <NUM> of <FIG> may be configured. The turbine engine <NUM> extends along an axial centerline (e.g., the centerline <NUM>) between an upstream airflow inlet <NUM> and a downstream airflow exhaust <NUM>. The turbine engine <NUM> includes a fan section <NUM>, a compressor section <NUM>, a combustor section <NUM> and a turbine section <NUM>. The compressor section <NUM> includes a low pressure compressor (LPC) section 147A and a high pressure compressor (HPC) section 147B. The turbine section <NUM> includes a high pressure turbine (HPT) section 149A and a low pressure turbine (LPT) section 149B.

The engine sections <NUM>-149B are arranged sequentially along the centerline <NUM> within an engine housing <NUM>. This 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 147A-149B; e.g., an engine core. This inner case <NUM> may include or may be connected to the static structure <NUM> of <FIG>. The outer case <NUM> may house at least the fan section <NUM>.

Each of the engine sections <NUM>, 147A, 147B, 149A and 149B 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. The rotating structure <NUM> of <FIG> may be configured as any one of the shafts <NUM>-<NUM> or a component rotatable therewith, and the bearing <NUM> of <FIG> may be configured as any one of the bearings <NUM>.

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 gas path <NUM> and a bypass gas path <NUM>. The core gas path <NUM> extends sequentially through the engine sections 147A-149B. The air within the core gas path <NUM> may be referred to as "core air". The bypass gas path <NUM> extends through a bypass duct, which bypasses the engine core. The air within the bypass gas path <NUM> may be referred to as "bypass air".

While each nozzle <NUM> is described above as directing the fluid towards (e.g., to) the bearing <NUM>, one or more or each of the nozzles <NUM> may also or alternatively be configured to direct the fluid towards another component within the rotational equipment (e.g., the gas turbine engine <NUM>). For example, the fluid may be directed to the seal land <NUM> (e.g., see <FIG>), a wall <NUM> of the compartment <NUM> (e.g., see <FIG>), an oil scoop, a seal seat and/or another component within the bearing compartment <NUM> or elsewhere that needs cooling and/or lubrication. The present disclosure therefore is not limited to delivering the fluid to any particular rotational equipment components.

While each guide rail <NUM> is described above as guiding movement (e.g., translation) of the seal support assembly <NUM> and its carrier <NUM>, one or more or each of the guide rails <NUM> may also or alternatively be configured for guiding movement (e.g., translation) of another component within the rotational equipment (e.g., the gas turbine engine <NUM>).

The assembly <NUM> may be included in various turbine engines other than the one described above as well as in other types of rotational equipment. The assembly <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 assembly <NUM> may be included in a turbine engine configured without a gear train. The assembly <NUM> may be included in a geared or non-geared turbine engine configured with a single spool, with two spools (e.g., see <FIG>), 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 or rotational equipment.

Claim 1:
An assembly (<NUM>) for rotational equipment, comprising:
a first component;
a static structure (<NUM>) comprising a static structure fluid passage (<NUM>);
a guide rail (<NUM>) mounted to the static structure (<NUM>), the guide rail (<NUM>) comprising a guide rail fluid passage (<NUM>) and a nozzle (<NUM>); and
a second component mated with and configured to translate along the guide rail (<NUM>),
wherein the first component comprises either a bearing (<NUM>), a seal land (<NUM>) or a compartment wall (<NUM>) for housing at least a bearing,
characterised in that:
the guide rail fluid passage (<NUM>) fluidly couples the static structure fluid passage (<NUM>) to a nozzle orifice (<NUM>) of the nozzle (<NUM>), and the nozzle (<NUM>) configured to direct fluid onto the first component through the nozzle orifice (<NUM>).