Patent Description:
At least some known gas turbine engines include one or more oil cooling systems that are configured to cool and lubricate components of gas turbine engines. Some gas turbine engines include an air-oil surface cooler and/or a fuel-oil heat exchanger. Air-oil heat exchangers attached to the inner radial surface of the nacelle, and use fan air to cool the oil flowing through the air-oil heat exchanger. Air-oil surface coolers include fins protruding into the bypass airflow passageway that exchange heat with the relatively cold fan air.

Fuel in aircraft engines is often heated to prevent water in the fuel from freezing and to improve combustion of the fuel. In some gas turbine engines relatively hot oil is used to heat the fuel. Air has typically not been used to heat the fuel. A leak in the fuel-oil heat exchanger could put fuel and oxygen in contact with each other inside the engine. Having separate air-oil and fuel-oil heat exchangers takes up valuable space in the engine and adds weight to the engine.

<CIT> is concerned with gas turbine heat exchangers, and methods of assembling the same. <CIT> is concerned with gas turbine heat exchangers, and methods of assembling the same. <CIT> is concerned with a dual seated by-pass valve for surface coolers. Another example of prior art solution is provided in document <CIT>.

In one aspect, a heat exchanger assembly according to claim <NUM> is provided.

In yet another aspect, a gas turbine engine according to claim <NUM> is provided.

Various features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:.

Although specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only.

Here and throughout the specification and claims, range limitations may be combined and/or interchanged; such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise.

The following detailed description illustrates embodiments of the disclosure by way of example and not by way of limitation. It is contemplated that the disclosure has general application to a method and system for cooling oil in an aircraft engine.

Embodiments of the heat exchanger assembly described herein cool oil in a gas turbine engine. The heat exchanger assembly includes a combined air-oil and fuel-oil heat exchanger located on an inner radial surface of a nacelle. The combined air-oil and fuel-oil heat exchanger includes a first flow path for channeling fuel through the heat exchanger, a second flow path for channeling oil through the heat exchanger, and a third flow path for directing air proximate an outer finned surface of the heat exchanger. The heat exchanger cools the oil by exchanging heat with fan air in the fan bypass duct and by exchanging heat with fuel. In an exemplary embodiment, the heat exchanger is configured to cool oil with fan air in the fan bypass duct and fuel simultaneously. The heat exchanger includes a plurality of fins disposed on the surface of the heat exchanger, which protrude into the fan bypass duct. The oil and fuel flow through one or more conduits included in the heat exchanger. The oil conduits are disposed within the heat exchangers between the surface of the heat exchanger and the fuel conduits to maintain a separation between the flow of fuel in the heat exchanger and the flow of air past the heat exchanger. In an exemplary embodiment, the oil conduits and fuel conduits are configured to flow in a countercurrent flow arrangement.

During operation, the heat exchangers receive relatively hot oil from the engine and relatively cool fuel from a fuel pump. Fan air in the fan bypass duct exchanges heat with the plurality of fins which exchange heat with the oil. The fuel simultaneously exchanges heat with the oil. The oil is cooled by the fan air and the fuel at the same time in the single heat exchanger. The heat exchanger returns the heated fuel and cooled oil to the engine. In an alternative embodiment, the oil conduits and fuel conduits are configured to flow in a co-flow arrangement. In another alternative embodiment, the heat exchangers are located on an outer radial surface of the engine.

The heat exchanger assemblies described herein offers advantages over known methods of cooling oil in a gas turbine engine. More specifically, some known heat exchanger systems use separate heat exchanger assemblies to cool oil with air and fuel. Heat exchanger system described herein combines the air and fuel cooling into a single heat exchanger assembly that facilitates reducing the weight of the heat exchange system and of the aircraft engine. Placing oil conduits between the fuel conduits and the fan bypass duct creates a buffer between the air and fuel.

<FIG> is a schematic cross-sectional view of a gas turbine engine in accordance with an exemplary embodiment of the present disclosure. In the example embodiment, the gas turbine engine is a high-bypass turbofan jet engine <NUM>, referred to herein as "turbofan engine <NUM>. " As shown in <FIG>, turbofan engine <NUM> defines an axial direction A (extending parallel to a longitudinal centerline <NUM> provided for reference) and a radial direction R. In general, turbofan <NUM> includes a fan section <NUM> and a core turbine engine <NUM> disposed downstream from fan section <NUM>.

Exemplary core turbine engine <NUM> depicted generally includes a substantially tubular outer casing <NUM> that defines an annular inlet <NUM>. Outer casing <NUM> encases, in serial flow relationship, a compressor section including a booster or low pressure (LP) compressor <NUM> and a high pressure (HP) compressor <NUM>; a combustion section <NUM>; a turbine section including a high pressure (HP) turbine <NUM> and a low pressure (LP) turbine <NUM>; and a jet exhaust nozzle section <NUM>. A high pressure (HP) shaft or spool <NUM> drivingly connects HP turbine <NUM> to HP compressor <NUM>. A low pressure (LP) shaft or spool <NUM> drivingly connects LP turbine <NUM> to LP compressor <NUM>. The compressor section, combustion section <NUM>, turbine section, and nozzle section <NUM> together define a core air flow path <NUM>.

For the embodiment depicted, fan section <NUM> includes a variable pitch fan <NUM> having a plurality of fan blades <NUM> coupled to a disk <NUM> in a spaced apart manner. As depicted, fan blades <NUM> extend outwardly from disk <NUM> generally along radial direction R. Each fan blade <NUM> is rotatable relative to disk <NUM> about a pitch axis P by virtue of fan blades <NUM> being operatively coupled to a suitable pitch change mechanism <NUM> configured to collectively vary the pitch of fan blades <NUM> in unison. Fan blades <NUM>, disk <NUM>, and pitch change mechanism <NUM> are together rotatable about longitudinal axis <NUM> by LP shaft <NUM> across a power gear box <NUM>. Power gear box <NUM> includes a plurality of gears for adjusting the rotational speed of fan <NUM> relative to LP shaft <NUM> to a more efficient rotational fan speed.

Referring still to the exemplary embodiment of <FIG>, disk <NUM> is covered by rotatable front hub <NUM> aerodynamically contoured to promote an airflow through plurality of fan blades <NUM>. Additionally, exemplary fan section <NUM> includes an annular fan casing or outer nacelle <NUM> that circumferentially surrounds fan <NUM> and/or at least a portion of core turbine engine <NUM>. Nacelle <NUM> includes an inner radial surface <NUM>. It should be appreciated that nacelle <NUM> may be configured to be supported relative to core turbine engine <NUM> by a plurality of circumferentially-spaced outlet guide vanes <NUM>. Moreover, a downstream section <NUM> of nacelle <NUM> may extend over an outer portion of core turbine engine <NUM> so as to define a bypass airflow passage <NUM> therebetween. A plurality of combined air-oil cooler and fuel-oil cooler heat exchangers <NUM> is disposed on inner radial surface <NUM> of nacelle <NUM> in bypass airflow passage <NUM>. In an alternative embodiment, a plurality of combined air-oil cooler and fuel-oil cooler heat exchangers <NUM> is disposed on outer radial surface <NUM> of outer casing <NUM> in bypass airflow passage <NUM>.

During operation of turbofan engine <NUM>, a volume of air <NUM> enters turbofan <NUM> through an associated inlet <NUM> of nacelle <NUM> and/or fan section <NUM>. As volume of air <NUM> passes across fan blades <NUM>, a first portion of air <NUM> as indicated by arrows <NUM> is directed or routed into bypass airflow passage <NUM> and a second portion of air <NUM> as indicated by arrow <NUM> is directed or routed into core air flow path <NUM>, or more specifically into LP compressor <NUM>. The ratio between first portion of air <NUM> and second portion of air <NUM> is commonly known as a bypass ratio. The pressure of second portion of air <NUM> is then increased as it is routed through HP compressor <NUM> and into combustion section <NUM>, where it is mixed with fuel and burned to provide combustion gases <NUM>. First portion of air <NUM> exchanges heat with combined air-oil cooler and fuel-oil cooler heat exchangers <NUM> disposed on inner radial surface <NUM> of nacelle <NUM> in bypass airflow passage <NUM>. In an alternative embodiment, first portion of air <NUM> exchanges heat with combined air-oil cooler and fuel-oil cooler heat exchangers <NUM> disposed on outer radial surface <NUM> of outer casing <NUM> in bypass airflow passage <NUM>.

Combustion gases <NUM> are routed through HP turbine <NUM> where a portion of thermal and/or kinetic energy from combustion gases <NUM> is extracted via sequential stages of HP turbine stator vanes <NUM> that are coupled to outer casing <NUM> and HP turbine rotor blades <NUM> that are coupled to HP shaft or spool <NUM>, thus causing HP shaft or spool <NUM> to rotate, thereby supporting operation of HP compressor <NUM>. Combustion gases <NUM> are then routed through LP turbine <NUM> where a second portion of thermal and kinetic energy is extracted from combustion gases <NUM> via sequential stages of LP turbine stator vanes <NUM> that are coupled to outer casing <NUM> and LP turbine rotor blades <NUM> that are coupled to LP shaft or spool <NUM>, thus causing LP shaft or spool <NUM> to rotate, thereby supporting operation of LP compressor <NUM> and/or rotation of fan <NUM>.

Combustion gases <NUM> are subsequently routed through jet exhaust nozzle section <NUM> of core turbine engine <NUM> to provide propulsive thrust. Simultaneously, the pressure of first portion of air <NUM> is substantially increased as first portion of air <NUM> is routed through bypass airflow passage <NUM> before it is exhausted from a fan nozzle exhaust section <NUM> of turbofan <NUM>, also providing propulsive thrust. HP turbine <NUM>, LP turbine <NUM>, and jet exhaust nozzle section <NUM> at least partially define a hot gas path <NUM> for routing combustion gases <NUM> through core turbine engine <NUM>.

It should be appreciated, however, that exemplary turbofan engine <NUM> depicted in <FIG> is by way of example only, and that in other exemplary embodiments, turbofan engine <NUM> may have any other suitable configuration. It should also be appreciated, that in still other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of the present disclosure may be incorporated into, e.g., a turboprop engine.

<FIG> is a schematic diagram of a heat exchanger assembly <NUM>. In the example embodiment, the heat exchanger assembly <NUM> is a combined air-oil and fuel-oil heat exchanger. Heat exchanger assembly <NUM> includes a surface <NUM> disposed on inner radial surface <NUM> (shown in <FIG>). Heat exchanger assembly <NUM> also includes a plurality of fin members <NUM> disposed on surface <NUM> and extending into bypass airflow passage <NUM> (shown in <FIG>). A plurality of first internal flow paths <NUM> is disposed within heat exchanger assembly <NUM>. Heat exchanger assembly <NUM> includes a plurality of first internal flow paths inlets <NUM> configured to receive oil and coupled in flow communication with first internal flow paths <NUM>. Heat exchanger assembly <NUM> also includes a plurality of first internal flow paths outlets <NUM> coupled in flow communication with first internal flow paths <NUM>. A plurality of second internal flow paths <NUM> is disposed within heat exchanger assembly <NUM>. Heat exchanger assembly <NUM> includes a plurality of second internal flow path inlets <NUM> configured to receive fuel and that are coupled in flow communication with second internal flow paths <NUM>. Heat exchanger assembly <NUM> also includes a plurality of second internal flow paths outlets <NUM> coupled in flow communication with second internal flow paths <NUM>. First internal flow path <NUM> is disposed radially inward with respect to second internal flow path <NUM>.

During operation, first portion of air <NUM> (shown in <FIG>) in bypass airflow passage <NUM> (shown in <FIG>) is configured to flow proximate to surface <NUM> and configured to exchange heat with fin members <NUM>. First internal flow paths inlets <NUM> are configured to receive a flow of oil. First internal flow paths inlets <NUM> are configured to deliver the flow of oil to first internal flow paths <NUM>. Oil in first internal flow paths <NUM> is configured to exchange heat with fuel in second internal flow paths <NUM> and with first portion of air <NUM> (shown in <FIG>) in bypass airflow passage <NUM> (shown in <FIG>). First internal flow paths <NUM> are configured to deliver oil to first internal flow paths outlets <NUM> which are configured to deliver oil to core turbine engine <NUM> (shown in <FIG>).

Second internal flow paths inlets <NUM> are configured to receive a flow of fuel. Second internal flow path inlets <NUM> are configured to channel the flow of fuel to first internal flow paths <NUM>. Fuel in second internal flow paths <NUM> is configured to exchange heat with oil in first internal flow path <NUM>. Second internal flow paths <NUM> are configured to deliver fuel to second internal flow paths outlets <NUM> which are configured to channel fuel to core turbine engine <NUM> (shown in <FIG>).

<FIG> is a schematic axial view of combined air-oil and fuel-oil heat exchanger assembly <NUM> shown in <FIG>. First internal flow path <NUM> is disposed within heat exchanger assembly <NUM> between surface <NUM> and second internal flow path <NUM>. In the event that fuel leaks from second internal flow path <NUM> toward surface <NUM>, first internal flow path <NUM> acts as a buffer to intercept leaking fuel before it reaches bypass airflow passage <NUM> (shown in <FIG>).

<FIG> is a schematic radial view of combined air-oil and fuel-oil heat exchanger assembly <NUM> shown in <FIG> configured in a countercurrent flow arrangement. First internal flow path <NUM> is configured flow oil in a first direction as indicated by arrow <NUM>. Second internal flow path <NUM> is configured to flow fuel in a second direction as indicated by arrow <NUM>. First direction <NUM> is opposite second direction <NUM>.

<FIG> is a schematic radial view of combined air-oil and fuel-oil heat exchanger assembly <NUM> shown in <FIG> configured in a co-current flow arrangement. First internal flow path <NUM> is configured to channel oil in a first direction as indicated by arrow <NUM>. Second internal flow path <NUM> is configured to channel fuel in a second direction as indicated by arrow <NUM>. First direction <NUM> is in substantially the same direction as second direction <NUM>.

In an alternative embodiment, combined air-oil and fuel-oil heat exchanger assembly <NUM> is disposed on outer radial surface <NUM> of outer casing <NUM> in bypass airflow passage <NUM>.

The above-described heat exchange assemblies provide an efficient method for cooling oil in a gas turbine engine. Specifically, the above-described heat exchange system combines an air-oil cooler and a fuel-oil cooler into a single heat exchanger. Combining the air-oil cooler and fuel-oil cooler into a single heat exchanger reduces the number of parts in an aircraft engine and reduces the complexity of the engine. As such, combining the air-oil cooler and fuel-oil cooler into a single heat exchanger reduces the weight of the engine. Additionally, locating the oil conduits between the fuel conduits and the bypass airflow passage creates a barrier between the fuel and the air. Creating a barrier between the air and the fuel reduces the likelihood that either will leak to the other.

Exemplary embodiments of combined air-oil cooler and fuel-oil cooler surface cooler are described above in detail. The combined air-oil cooler and fuel-oil cooler surface cooler, and methods of operating such systems and devices are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the methods may also be used in combination with other systems requiring oil cooling, and are not limited to practice with only the systems and methods as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other machinery applications that are currently configured to receive and accept combined air-oil cooler and fuel-oil cooler surface cooler.

Example methods and apparatus for cooling oil with air and fuel are described above in detail. The apparatus illustrated is not limited to the specific embodiments described herein, but rather, components of each may be utilized independently and separately from other components described herein. Each system component can also be used in combination with other system components.

Claim 1:
A heat exchanger assembly (<NUM>) for a gas turbine engine comprising:
an arcuate unitary body having:
a first internal flow path (<NUM>) configured to channel a flow of oil to be cooled from a first inlet (<NUM>) to a first outlet (<NUM>), the first internal flow path being enclosed within and formed integrally with the unitary body;
a second internal flow path (<NUM>) in thermal communication with the first internal flow path and configured to channel a flow of a first coolant from a second inlet (<NUM>) to a second outlet (<NUM>), wherein the first coolant comprises fuel, and wherein the second internal flow path is not in fluid communication with the first internal flow path, and the second internal flow path is enclosed within and formed integrally with the unitary body; and
an external flow path (<NUM>) configured to receive a flow of a second coolant proximate a circumferentially extending surface (<NUM>) of the unitary body, the external flow path including a plurality of metallic fins.