Fuel manifold adapter

A fuel manifold adapter for a fuel system of an aircraft engine, the fuel manifold adapter comprising: a body having a body-output interface defining a downstream end of a body passage including a body bore about a bore axis, the body-output interface movably and fluidly connectable to a first component of the fuel system mounted to a first mounting point of the engine, and a body-input interface defining an upstream end of the body passage, the body-input interface rigidly and fluidly connectable to a second component of the fuel system mounted to a second mounting point of the engine, and a transfer tube having an upstream-tube end slidably engaged with the body along the bore axis via the body bore, the transfer tube having a downstream-tube end opposite the upstream-tube end slidably engageable along the bore axis with the first component, the downstream-tube end defining a downstream end of the fuel manifold adapter relative to fuel flow through the fuel manifold adapter.

TECHNICAL FIELD

This disclosure relates generally to fluid transfer and, more particularly, to a fuel manifold adapter for transferring fuel in, for example, a fuel transfer system for a gas turbine engine or the like.

BACKGROUND OF THE ART

Various systems are known in the art for transferring fuel between a fuel source and a fuel nozzle of a gas turbine engine. While these known systems may suit their intended purpose, there remains room for improvement in the art.

SUMMARY

In an aspect of the present technology, there is provided a fuel manifold adapter for a fuel system of an aircraft engine, the fuel manifold adapter comprising: a body having a body-output interface defining a downstream end of a body passage including a body bore about a bore axis, the body-output interface movably and fluidly connectable to a first component of the fuel system mounted to a first mounting point of the engine, and a body-input interface defining an upstream end of the body passage, the body-input interface rigidly and fluidly connectable to a second component of the fuel system mounted to a second mounting point of the engine, and a transfer tube having an upstream-tube end slidably engaged with the body along the bore axis via the body bore, the transfer tube having a downstream-tube end opposite the upstream-tube end slidably engageable along the bore axis with the first component, the downstream-tube end defining a downstream end of the fuel manifold adapter relative to fuel flow through the fuel manifold adapter.

In another aspect of the present technology, there is provided a fuel manifold adapter interchangeably connectable between respective fuel manifolds and fuel sources of different aircraft engine platforms, the fuel manifold adapter comprising: a body having a body-input interface and a body-output interface, the body-input interface rigidly connectable to the fuel source of a given one of the different engine platforms so as to locate the body-output interface in alignment with a nozzle-input interface of the fuel manifold of the given one of the engine platforms, the body-output interface slidably engaged with an upstream-tube end of a linear transfer tube having a downstream-tube end slidably engaged with the nozzle-input interface, the body-output interface and the nozzle-input interface slidably engaged via the linear transfer tube and thermally decoupled via the linear transfer tube.

In yet another aspect of the present technology, there is provided an aircraft engine comprising: a fuel manifold having an inlet nozzle, the fuel manifold mounted at a first mounting point of the aircraft engine, the inlet nozzle having a nozzle bore facing in a first direction; a fuel source mounted at a second mounting point of the aircraft engine, the fuel source having a source bore facing in a second direction; a fuel manifold adapter in fluid communication between the fuel source and the inlet nozzle, the fuel manifold adapter including: a body defining a body bore about a bore axis; a transfer tube having an upstream-tube end slidably engaged with the body along the bore axis via the body bore, and a downstream-tube end opposite the upstream-tube end slidably engaged with the inlet nozzle along the bore axis via the nozzle bore; a flanged connector extending along a connector axis, the flanged connector matingly engaged along the connector axis with and fastened to the fuel source via the source bore, and a conduit routed from a downstream-conduit end in fluid communication with the body bore to an upstream-conduit end in fluid communication with the flanged connector.

DETAILED DESCRIPTION

FIG.1illustrates an aircraft engine10of a type preferably provided for use in subsonic flight. According to the illustrated example, the engine10is a turboshaft gas turbine engine generally comprising in serial flow communication a compressor12for pressurizing the air, a combustor16in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section18for extracting energy from the combustion gases. There will now be described a fuel manifold adapter100(the adapter100) used in a hot section of the engine, generally shown at L1, in connection with a fuel manifold20(FIG.2) of a fuel system of the engine10located proximate to the combustor16.

Turning now toFIG.2, the adapter100is disposed in fluid communication between a fuel inlet nozzle30(the inlet nozzle30) supported by a first mount40(or flange40of the inlet nozzle30), and a fuel source50(the source50) for instance provided in the form of a flow divider valve and supported by a second mount60(or bracket60of the source50). The inlet nozzle30and the source50are also respectively referred to as a first component and a second component of the fuel system of the engine10. Via the first mount40and the second mount60, the inlet nozzle30and the source50are respectively mounted at a first mounting point of the engine10and at a second mounting point of the engine10each being susceptible to thermal growth. Due to the thermal growth occurring as the engine10operates, the first and second mounting points move relative to one another with their respective mounted components. In the illustrated embodiment, the first mounting point is on a turbine support case of the engine10. The first mount40is integral to the inlet nozzle30and fastened directly to the turbine support case. The second mounting point is located fore of the first mounting point on a peripheral flange of the turbine support case. The second mounting point is also located radially outward of the first mounting point relative to a center line CL of the engine10(FIG.1). In other embodiments, the second mounting point is located aft of the first mounting point, for example on a turbine exhaust case of the engine10.

The adapter100includes a body110that is held in position fixedly relative to the source50yet movably relative to the inlet nozzle30so as to mitigate stresses imparted to the inlet nozzle30by the adapter100as the body110moves with the source50to and from the inlet nozzle30. The body110is mounted at a third mounting point of the engine10via a third mount150(or bracket150of the body110), supporting the adapter100in position relative to the source50. The third mounting point is located aft of the first mounting point, on a peripheral flange of the turbine exhaust case of the engine10. In other embodiments, the third mount150is integral to the body110(as shown for example inFIG.3). In yet other embodiments, the body110could be mounted to the source50(as shown for example inFIG.8) and the third mount150could be omitted.

A body-output interface112of the body110movably interfaces with a nozzle-input interface32(or upstream end of the inlet nozzle30) via a transfer tube assembly120located at a downstream end (or output end) of the adapter100. The transfer tube assembly120may be said to thermally and dynamically decouple the body-output interface112and a remainder of the adapter100from the inlet nozzle30. At an upstream end (or input end) of the adapter100, a body-input interface114of the body110fixedly interfaces with a source-output interface52(or downstream end of the source50) via a flanged connector130and a conduit140. The conduit140comprises a rigid tube routed from the flanged connector130to the body110. The conduit140and the flanged connector130can also be described as a rigid supply line which, depending on the embodiment, can form part of the adapter100or the source50. In this embodiment, the supply line forms part of the adapter100. The conduit140may be said to rigidly connect the flanged connector130and the body110to one another. A fuel path through the adapter100extending from the source50to the inlet nozzle30is defined successively by the flanged connector130, the conduit140, the body110and the transfer tube assembly120. The fuel path can consist of a primary fuel path and a secondary fuel path both routed through the adapter100separately from one another. The forthcoming description will focus on features of the adapter100defining the primary fuel path, as corresponding features of the adapter100defining the secondary fuel path are similar, unless stated otherwise.

Still referring toFIG.2, according to the illustrated embodiment, the inlet nozzle30interfaces with the first mounting point via the first mount40so as to orient the nozzle-input interface32in a first direction D1having an axial component parallel to the center line CL of the engine10. In the first direction D1, the nozzle-input interface32extends aft relative to the first mounting point. The second mount60holds the source50so as to orient the source-output interface52in a second direction D2having an axial component parallel to the center line CL of the engine10. The first direction D1and the direction D2are in this arrangement parallel to one another and to the center line CL of the engine10, although other arrangements are possible. Also, the nozzle-input interface32and the source-output interface52are positioned so as to be radially close to one another relative to the center line CL. This disposition allows the adapter100to have a minimal radial footprint as it extends from the source-output interface52to the nozzle-input interface32. As such, the inlet nozzle30, the source50and the adapter100can be made to fit inside a radially outer envelope of the turbine section18defined by the outside of the turbine support and exhaust cases up to a radially outer limit of the engine10.

The adapter100is positioned such that the body-output interface112is oriented opposite the first direction D1across from the nozzle-input interface32and the body-input interface114is oriented in such a way that the flanged connector130rigidly connected thereto is oriented opposite the second direction D2across from the source-output interface52. The connections between the body110and the inlet nozzle30and between the body110and the source50are directional. Indeed, connecting the body-output interface112to the nozzle-input interface32via the transfer tube assembly120places the body-input interface114in an orientation suitable for it to be connectable to the source-output interface52via the supply line. Also, upon the supply line being connected to the body110, connecting the body-output interface112to the nozzle-input interface32orients the flanged connector opposite the second direction D2in alignment with the source-output interface52. Conversely, upon the supply line being connected to the body110, connecting the body-input interface114to the source-output interface52via the supply line orients the body-output interface112opposite the first direction D1in alignment with the nozzle-input interface32.

Upstream of the fuel path, the source-output interface52defines a port54from which fuel is flowed to the adapter100, and to which the flanged connector130is fluidly connected. The flanged connector130has a flange132and a cylinder134, or cylindrical fitting (similar to that illustrated inFIG.11with respect to another embodiment) projecting from the flange132along a connector axis C. The port54is shaped complementarily to the cylinder134, in this case a bore extending along a port axis P oriented in the second direction D2by the second mount60. Upon the flanged connector130being connected to the port54, the connector and port axes C, P are collinear. A fastening means of the flanged connector130, in this case bolts mechanically coupled to complementary bores defined by the flange132and the source-output interface52, determines an orientation of the supply line with respect to the port axis P as it fastens the supply line to the source-output interface52. By orienting the supply line together with the body110with respect to the port axis P, the flanged connector130is used to locate the body-output interface112in alignment with the nozzle-input interface32.

Referring toFIGS.3to7, fuel-path defining features will now be described with respect to another embodiment of the adapter100. Downstream of the source50, the primary fuel path is defined by the supply line, i.e., by the flanged connector130and the conduit140, successively. Downstream of the supply line, the primary fuel path is defined a first passage116extending through the body110. The body-input interface114defines an upstream end116bof the first passage116to which the conduit140is fluidly connected. The body-output interface112of the body110is cylindrical in shape and extends along a body axis B (FIG.4). The body-output interface112defines a downstream end116aof the first passage116in fluid communication with the upstream end116b, also referred to as a first body bore116aof the body110.

Downstream of the source50, the secondary fuel path is defined by a second supply line, i.e., by a second flanged connector130′ and a second conduit140′, successively. Downstream of the second supply line, the secondary fuel path is defined a second passage116′ extending through the body110. The body-input interface114defines an upstream end116b′ of the second passage116′ to which the second conduit140′ is fluidly connected. The body-output interface112defines a downstream end116a′ of the second passage116in fluid communication with the upstream end116b′, also referred to as a second body bore116a′ of the body110.

The nozzle-input interface32is located downstream of the body-output interface112across from the transfer tube assembly120. The nozzle-input interface32is cylindrical in shape (as shown inFIGS.6and7), and extends along a longitudinal axis N (FIG.3) oriented in the first direction D1by the first mount40. A first nozzle bore34and a second nozzle bore34′ extend in the nozzle-input interface32in fluid communication with the fuel manifold20.

With reference toFIGS.6and7, characteristics pertaining to the transfer tube assembly120and its relationship with the body-output interface112and the nozzle-input interface32will now be described. The transfer tube assembly120includes a first transfer tube122having a rigid, tubular body extending along a longitudinal axis A from a first tube end122ato a second tube end122b. The first tube end122ais slidably received by the first body bore116a, whereas the second tube end122bextends to outside the first body bore116aso as to be slidably receivable by the first nozzle bore34upon the body110being suitably positioned relative to the inlet nozzle30. Around either ends122a,122bof the transfer tube122, O-rings124may be mounted for sealing engagement with the corresponding bores, thereby sealing a passage from one bore to the other via the transfer tube122. A second transfer tube122′ of the transfer tube assembly120has a rigid, tubular body extending along a longitudinal axis A′ from a first tube end122a′ to a second tube end122b′. The first tube end122a′ is slidably received by the second body bore116a′, whereas the second tube end122b′ extends to outside the second-body bore116a′ so as to be slidably receivable by the second nozzle bore34′ upon the body110being suitably positioned relative to the inlet nozzle30.

According to some embodiments, the transfer tube assembly120includes a drain sleeve126extending around the transfer tube122from around the body-output interface112to around the nozzle-input interface32. As shown inFIG.6, O-rings124may be mounted around the nozzle-input interface32and the body-output interface112for sealing engagement with an inner cylindrical surface of the drain sleeve126, thereby defining extremities of a sealed cavity inside the drain sleeve126. However, the drain sleeve126may be omitted depending on the implementation.

InFIGS.8and9, there is shown yet another embodiment of the adapter100implemented in a turboshaft engine. In this embodiment, the first mounting point is located on the turbine support case and the second mounting point is located on the peripheral flange of the turbine support case fore of the first mounting point. The third mounting point is located on the source50, i.e., the body110is supported by virtue of its connection to the source50. The body110may be said to be located axially between the inlet nozzle30and the source50relative to the center line of the engine10. The nozzle-input interface32extends in the first direction D1fore relative to the first mounting point and toward the second mounting point. The first direction D1may thus be said to be toward the source50. This arrangement of the inlet nozzle30relative to the source50allows for an axially-compact adapter100.

In this embodiment, first and second flanged connectors130,130′ connect to the body110by way of first and second conduits140,140′, provided in the form of hollow and axially short arms that are integral to the body. The first and second conduits140,140′ project from the body-input interface114transversely to the body axis B of the body-output interface112. The nozzle-input interface32is closer to a first port54of the source50than to a second port54′ of the source50. As such, the first conduit140is shorter than the second conduit140′. The first flanged connector130is of a type similar to that described hereinabove, having a first-connector flange132and a first-connector cylinder134, or cylindrical fitting, projecting therefrom along a first-connector axis C for mating engagement with the first port54along a first-port axis P. The second flanged connector130′ has a second-connector flange132′ and a second-connector bore134′ extending inward thereof along a second-connector axis C′. The second-connector bore134′ is in fluid communication with the second port54′ of the source-output interface52. A third transfer tube122a″ of the adapter100has a first end122a″ slidably engaged with the second flanged connector130′ via the second-connector bore134′ along the second-connector axis C′, and a second end122b″ opposite the first end122a″ slidably engaged with the source-output interface52via the second port54′ along a second-port axis P′. The source-output interface52is arranged such that the first-port axis P and the second-port axis P′ are generally parallel and aligned with the second direction D2, thereby allowing the first flanged connector130to matingly engage the first port54simultaneously as the second flanged connector130′ engages with the second port54′ via the third transfer tube122″. Under certain circumstances, the second-port axis P′ may be misaligned (e.g., be at an angle of between 0 to 4 degrees) relative to the first-port axis P, due for example to thermal deformation of the source50and/or to manufacturing tolerances. As the first flanged connector130matingly engages the first port54with the first-connector axis C collinear to the first-port axis P, the third transfer tube122″ may tilt relative to the second-connector axis C′ and/or to the second-port axis P′ to accommodate such misalignment while maintaining the fluid communication between the second port54′ and the second flanged connector130′.

The present disclosure is not limited to aircraft engines of the turboshaft gas turbine type. For instance, inFIGS.10and11, there is shown an embodiment of the fuel manifold adapter100implemented in an engine of the turboprop type. In this embodiment, the first mounting point is located on the turbine support case, the second mounting point is located on the turbine exhaust case at a location spaced aft and circumferentially from the first mounting point, and the third mounting point is located on the peripheral flange of the turbine support case. The nozzle-input interface32is oriented in the first direction D1aft relative to the first mounting point, whereas the source-output interface52is oriented in the second direction D2fore relative to the second mounting point and at an angle relative to the first direction D1. Thus, the first direction D1and the second direction D2are neither the same nor opposite one another. Nevertheless, such differences in location and orientation of the nozzle-input interface32and the source-output interface52are compensated by the supply line being suitably routed therebetween. With the body110located such that the body-output interface112is in alignment with the nozzle-input interface32opposite the first direction D1, the supply line is routed from the body-input interface114so as to extend opposite the second direction D2as it nears the source-output interface52.

It shall be noted that the same body110can also be used in connection to the inlet nozzle30of a turboshaft engine, as shown inFIG.2, provided that the supply line is suitably routed between the body-input interface114of the body110and the source-output interface52of the source50of the turboshaft engine. The adapter100can thus be said to be interchangeably connectable between respective fuel manifolds and fuel sources of different aircraft engine platforms.