Exhaust system for a turbomachine comprising a heat exchanger
The exhaust system for turbomachines addresses the challenge of heat recovery by using a compact heat exchanger on a nozzle to exchange heat with a fluid, achieving efficient heat recovery without significant pressure losses and maintaining turbomachine compactness.
Patent Information
- Application Number
- FR2022008020
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2022-08-02
- Publication Date
- 2025-06-27
- Estimated Expiration
- 2042-08-02
AI Technical Summary
Existing exhaust systems for turbomachines face challenges in efficiently recovering heat from exhaust gases without inducing significant pressure losses, which negatively impacts the performance and compactness of the turbomachine.
The proposed exhaust system incorporates a compact heat exchanger positioned on a nozzle, featuring a distributor, collector, and pipes to circulate a heat transfer fluid, allowing for heat exchange between the exhaust gas stream and the heat transfer fluid without obstructing the primary exhaust flow.
This solution enables efficient heat recovery at the periphery of the exhaust stream, minimizing pressure losses and maintaining the compactness of the turbomachine, thereby enhancing performance and reducing environmental impact.
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Abstract
Description
Title of the invention: Exhaust system for a turbomachine comprising a heat exchanger Technical field
[0001] The present invention relates to the recovery of heat at the exhaust of a turbomachine.
[0002] In particular, the present invention relates to the recovery of heat for the purpose of heating fuel and / or air intended to enter a combustion chamber of said turbomachine.
[0003] Generally, the invention applies to any type of exhaust system. Prior art
[0004] [Fig.l] schematically shows a turbomachine 2 of an aircraft according to the state of the art. The turbomachine 2 comprises a fan 4 for recovering air from the atmosphere outside the turbomachine 2, a compressor 6, a combustion chamber 8, a turbine 10, and an exhaust system 12. With a view to improving the performance of the turbomachines, it is possible to heat air leaving the compressor 6 and / or fuel and / or entering the combustion chamber 8 with the air.
[0005] A heat source located nearby is preferred so as to increase the thermal efficiency of the turbomachine 2. A heat source is for example constituted by the gases exiting through the exhaust system 12, downstream of the turbine 10. However, the positioning of a heat exchanger in the primary exhaust flow 14, for example in the form of fins positioned in the flow, induces pressure losses of the turbomachine 2, which negatively impacts the thrust of the aircraft. The positioning of a heat exchanger in the turbomachine 2 also harms the compactness of said turbomachine 2. Statement of the invention
[0006] The present invention therefore aims to overcome the aforementioned drawbacks and to provide an exhaust system allowing the efficient recovery of heat at the exhaust of a turbomachine. To this end, the invention is the result of technological research aimed at very significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.
[0007] The present invention relates to an exhaust system for a turbomachine comprising a nozzle delimiting at least in part a gas exhaust stream, the exhaust system further comprising a heat exchanger comprising at least one distributor, at least one collector and pipes configured to circulate a heat transfer fluid in said pipes between the distributor and the collector, the heat exchanger being configured to carry out heat exchanges between the gas exhaust stream and the pipes, and the heat exchanger being positioned on the nozzle, the pipes being partially formed from a surface of the nozzle.
[0008] Thus, the exhaust system according to the invention allows the recovery of heat at the exhaust of a turbomachine at the periphery of the exhaust stream without inducing significant pressure losses for the turbomachine, the heat exchanger being particularly compact and non-invasive.
[0009] Preferably, the nozzle comprises an annular external portion and a central body, the heat exchanger being positioned on the external portion and / or on the central body.
[0010] Advantageously, the external part of the nozzle comprises one or more annular sectors.
[0011] In various embodiments, the pipes are positioned outside or inside the gas exhaust vein.
[0012] In one embodiment, the pipes have a cross-section of semi-circular, or rectangular, or bell-shaped, or semi-elliptical, or triangular shape.
[0013] Advantageously, the pipes extend longitudinally parallel to a longitudinal axis of the exhaust system, or transversely to the longitudinal axis.
[0014] In one embodiment, the exhaust system is made of a material comprising a titanium alloy and / or a nickel alloy.
[0015] Advantageously, the heat exchanger is configured to carry out heat exchanges between exhaust gases exiting through the gas exhaust stream and a heat transfer fluid circulating in the pipes, said heat transfer fluid comprising air and / or water vapor and / or water and / or fuel and / or oil and / or supercritical CO2 and / or liquid or gaseous hydrogen.
[0016] The present invention also relates to a turbomachine comprising a compressor, a combustion chamber and an exhaust system as defined previously, the heat exchanger being configured to heat fuel at the inlet of the combustion chamber and / or air at the outlet of the compressor before entering the combustion chamber.
[0017] The present invention also relates to an aircraft comprising a turbomachine as defined previously and / or an exhaust system as defined previously.
[0018] The present invention further relates to the use of the exhaust system as defined above in a thermal management system for heating air or fuel in a turbomachine. Brief description of the drawings
[0019] Other aims, characteristics and advantages of the invention will appear on reading the following description, given solely by way of non-limiting example, and made with reference to the appended drawings in which:
[0020] [Fig-1] is a longitudinal and schematic sectional view of a turbomachine of a aircraft according to the state of the art;
[0021] [Fig.2] is a longitudinal and schematic sectional view of a turbomachine of a aircraft according to the invention;
[0022] [Fig.3] is a schematic view of a first embodiment of a system exhaust for turbomachine according to the invention;
[0023] [Fig.4] is a schematic view of a first variant of the first mode of rea construction of an exhaust system for a turbomachine illustrated in [Fig.3];
[0024] [Fig.5] is a schematic view of a second variant of the first mode of rea construction of an exhaust system for a turbomachine illustrated in [Fig.3];
[0025] [Fig.6] is a schematic view of a third variant of the first mode of rea construction of an exhaust system for a turbomachine illustrated in [Fig.3];
[0026] [Fig.7] is a schematic view of a second embodiment of a system exhaust for turbomachine according to the invention;
[0027] [Fig.8] is a schematic view of the first embodiment of a system exhaust of [Fig.3] comprising an outer skin;
[0028] [Fig.9] is a schematic sectional view of pipes whose cross-section is semicircular; and
[0029] [Fig. 10] is a schematic sectional view of pipes whose section transversal is triangular. Detailed description of at least one embodiment
[0030] [Fig. 2] schematically shows a turbomachine 16 of an aircraft according to the invention. The turbomachine 16 comprises a fan 4 for recovering air from the atmosphere outside the turbomachine 16, a compressor 6, a combustion chamber 8, a turbine 10, and an exhaust system 18.
[0031] In particular, the exhaust system 12 comprises a nozzle 20 preferably comprising an annular external part 21 and a central body 22 forming an exhaust stream 24 of gas of annular section. The exhaust system 18 also comprises a heat exchanger 26 configured to heat fuel at the inlet of the combustion chamber 8 and / or air at the outlet of the compressor 6 and before entry into the combustion chamber 8.
[0032] [Fig.3] shows schematically a first embodiment of a exhaust system 18 in which the heat exchanger 26 is positioned on the external part 21 of the nozzle 20, the central body 22 not being shown in [Fig. 3] as well as in the following figures. Alternatively, by analogy, the heat exchanger 26 can be positioned on the central body 22 of the exhaust system 18.
[0033] The heat exchanger 26 comprises at least one distributor 28, at least one collector 30 and pipes 32.
[0034] The distributor 28 is configured to inject a heat transfer fluid into the pipes 32 themselves configured to circulate said heat transfer fluid in said pipes 32 to a collector 30 configured to recover the heated heat transfer fluid.
[0035] The heat transfer fluid comprises for example air, and / or water vapor, and / or water, and / or fuel, and / or oil, and / or supercritical CO2 and / or liquid hydrogen, and / or fuel for supplying the turbomachine 16. Liquid hydrogen can for example be used as fuel and is advantageously used as heat transfer fluid since it is a cold fuel, its boiling point being approximately 20 Kelvin.
[0036] The pipes 32 are partially formed from a surface 34 of the external part 21 of the nozzle 20 or from a surface of the central body where appropriate. The surface is a surface of the wall of the nozzle, also called the primary exhaust wall, in contact with which the exhaust gases are expelled.
[0037] The pipes 32, as well as the distributors 28 and collectors 30 are positioned in a preferred manner on the outer surface 34 of the wall of the outer part 21 of the nozzle 20, in other words outside the exhaust stream 24 so as not to disturb the exhaust flow. As a variant, the pipes 32 can nevertheless be positioned on the inner surface of the wall of the nozzle 20, in other words inside the exhaust stream 24. Advantageously, the pipes 32 are distributed over the entire periphery of the exhaust stream 24.
[0038] Thus, the heat exchanger 26 is configured to carry out heat exchanges between the gas exhaust stream 24 and the pipes 32 via the wall(s) of the nozzle 20.
[0039] The exhaust system 18 as shown in [Fig. 3] comprises four annular sectors 36 of substantially the same dimensions, at least one manifold 30, at least one distributor 28 and pipes 32 being positioned on each sector 36, the manifold 30 and distributor 28 adjoining two different sectors 36 being connected by a tube 38. As a variant, the exhaust system 18 comprises a single annular sector or several annular sectors.
[0040] In the embodiment illustrated in [Fig. 3], the pipes 32 extend along the periphery of the external part 21 of the nozzle 20, transversely to the axis longitudinal L of the exhaust system 18.
[0041] In addition, the heat exchanger 26 comprises non-bent pipes 32, the only curvature of which is the curvature of the external part 21 of the nozzle 20.
[0042] A first variant of the first embodiment is shown schematically in [Fig.4].
[0043] In this first variant, the pipes 32 extend along the periphery of the external part 21 of the nozzle 20 in a serpentine fashion. In particular, the pipes 32 have bends 40 with an angle substantially equal to 180° so that each collector 30 and distributor 28 comprises few inlets and outlets to the pipes 32, in order to minimize the flow rate of fluid passing through the exchanger.
[0044] [Fig. 5] shows schematically a second variant of the first embodiment. This variant is identical to the embodiment of [Fig. 3], except that the pipes 32 extend longitudinally and substantially parallel to the longitudinal axis L of the exhaust system 18.
[0045] [Fig. 6] schematically shows a third variant of the first embodiment. This variant is identical to the embodiment of [Fig. 4], except that the pipes 32 extend longitudinally and substantially parallel to the longitudinal axis L of the exhaust system 18. The pipes 32 also have bends 40 with an angle substantially equal to 180°.
[0046] [Fig. 7] schematically shows a second embodiment of an exhaust system 18 in which the heat exchanger 26 is positioned on the external part 21 of the nozzle 20.
[0047] In this embodiment, the pipes 32 are positioned inside the exhaust vein 24 while the distributors 28 and manifolds 30 are positioned outside the exhaust vein 24. The pipes 32 extend substantially parallel to the longitudinal axis L of the exhaust system 18.
[0048] This embodiment makes it possible to increase the heat exchange surface, to the detriment of a slight loss of load of the primary flow of the turbomachine.
[0049] In each embodiment, the exhaust system 18 is made of a thermally resistant material, for example a material comprising a titanium alloy and / or a nickel alloy.
[0050] In each embodiment, the exhaust system 18 may optionally comprise an outer skin 42, as illustrated in [Fig. 8], arranged annularly around the heat exchanger 18 and serving as an aerodynamic fairing for the flow of the secondary stream or any other flow from the turbomachine. The exhaust system may also comprise a flange 44 at the longitudinal end of the nozzle 20 so as to attach said nozzle 20 to the turbomachine 2.
[0051] In various embodiments, the pipes 32 have, for example, a cross-section of semi-circular, rectangular, bell-shaped, semi-elliptical, or triangular shape. The shape of the cross-section of the pipes 32 also allows the pipes to be easily demolded during their manufacture.
[0052] [Fig. 9] schematically shows a sectional view of pipes 32 whose cross-section is semi-circular. The sectional view is here taken along the longitudinal axis of the exhaust system 18. The pipes 32 shown are, for example, the pipes 32 presented in the embodiment of [Fig. 3]. They are protected by the outer skin 42.
[0053] [Fig. 10] shows a sectional view of pipes 32 whose cross-section is triangular. The sectional view is made transversely to the longitudinal axis L of the exhaust system 18. The pipes 32 shown are for example the pipes 32 presented in the embodiment of [Fig. 7], in which the pipes 32 are positioned in the exhaust stream 24 and extend parallel to the longitudinal axis L of the exhaust system. The triangular section of the pipes 32 allows a large heat exchange surface and a low pressure drop. In addition, one of the sides of each pipe 32 is advantageously oriented radially in the direction of the longitudinal axis L, thus allowing easier demolding during the manufacture of the exhaust system 18.
[0054] Furthermore, for each embodiment, the manufacturing is preferably carried out by diffusion welding of a stack of several sheets, an inert gas being injected at the desired location of the pipes 32. Diffusion welding makes it possible to avoid a reduction at the welds, and thus makes it possible to produce an exhaust system 18 having substantially the same properties as if the latter were made from a single piece.
Claims
Claims
1. Exhaust system (18) for a turbomachine (16) comprising a nozzle (20) at least partially delimiting a gas exhaust stream (24), characterized in that it comprises a heat exchanger (26) comprising at least one distributor (28), at least one collector (30) and pipes (32) configured to circulate a heat transfer fluid in said pipes (32) between the distributor (28) and the collector (30), the heat exchanger (26) being configured to carry out heat exchanges between the gas exhaust stream (24) and the pipes (32), and the heat exchanger (26) being positioned on the nozzle (20), the pipes (32) being partially formed from a surface (34) of the nozzle (20).
2. Exhaust system according to claim 1, wherein the nozzle (20) comprises an annular external part (21) and a central body (22), the heat exchanger (26) being positioned on the external part (21) and / or on the central body (22).
3. Exhaust system according to claim 2, wherein the external part (21) of the nozzle (20) comprises one or more annular sectors (36).
4. An exhaust system according to any one of claims 1 to 3, wherein the pipes (32) are positioned outside or inside the gas exhaust stream (24).
5. An exhaust system according to any one of claims 1 to 4, wherein the pipes (32) extend longitudinally parallel to a longitudinal axis (L) of the exhaust system, or transversely to the longitudinal axis (L).
6. Exhaust system according to any one of claims 1 to 5, made of a material comprising a titanium alloy and / or a nickel alloy.
7. Exhaust system according to any one of claims 1 to 6, wherein the heat exchanger (26) is configured to carry out heat exchanges between exhaust gases exiting through the gas exhaust stream (24) and a heat transfer fluid circulating in the pipes (32), said heat transfer fluid comprising air and / or water vapor and / or water and / or fuel and / or oil and / or supercritical CO2 and / or liquid or gaseous hydrogen.
8. Turbomachine (16) comprising a compressor (6) and a chamber combustion (8), characterized in that it comprises an exhaust system (18) according to any one of claims 1 to 7, the heat exchanger (26) being configured to heat fuel at the inlet of the combustion chamber (8) and / or air at the outlet of the compressor (6) before entering the combustion chamber (8).
9. Aircraft characterized in that it comprises a turbomachine (16) according to claim 8 or an exhaust system (18) according to any one of claims 1 to 7.
10. Use of the exhaust system (18) according to any one of claims 1 to 7 in a thermal management system for heating air or fuel in a turbomachine (16).