WO2021121976A1

WO2021121976A1 - Gas turbine engine of an aircraft having oil cooling

Info

Publication number: WO2021121976A1
Application number: PCT/EP2020/084148
Authority: WO
Inventors: Ulrich Schulze; Markus Blumrich; Thomas JÄGER
Original assignee: Rolls-Royce Deutschland Ltd & Co Kg
Priority date: 2019-12-19
Filing date: 2020-12-01
Publication date: 2021-06-24
Also published as: DE102019135339A1

Abstract

The invention relates to a gas turbine engine (1) of an aircraft, comprising an inner engine region (27) and an outer engine region (28), which delimit a flow cross-section (2) and are operatively interconnected by means of braces (22, 22A to 22F). Oil can be led from a return (31) of the device (12), in the region of which return the operating temperature is greater than the temperature of the air that can be led through the flow cross-section (2), through at least one of the braces (22, 22A to 22F) from the inner engine region (27) into the outer engine region (28) and/or from the outer engine region (28) into the inner engine region (27) in order to cool the oil.

Description

GAS TURBINE ENGINE OF AN AIRCRAFT WITH OIL COOLING

The present disclosure relates to a gas turbine engine of an aircraft with at least one inner engine area and with at least one outer engine area.

From WO 2019/086065 A1 a fluid flow machine is known which comprises an intermediate channel or a flow cross section for air. The inter mediate channel is bounded radially by an outer engine area and an inner engine area. The inner engine area and the outer engine area are operatively connected to one another via struts which run radially through the flow cross-section and are spaced apart from one another in the circumferential direction of the flow cross-section. At least one of the struts is hollow and designed with minimal wall thickness in order to be able to lead supply lines, such as oil lines, through the interior of the strut and thus through the flow cross-section.

Furthermore, FR 3030627 B1 describes a turbomachine or a gas turbine engine with a flow cross section which is arranged between an inner engine area and an outer engine area. The inner engine area and the outer engine area are connected to one another via struts which run radially through the flow cross-section and are spaced apart from one another in the circumferential direction of the flow cross-section. Oil lines, electrical lines and the like can be guided through the struts in order to hydraulically or electrically couple a devices of the inner engine area with devices of the outer engine area to one another. The flow cross-section is limited by what is known as an intermediate housing, which comprises two annular housing areas arranged coaxially with one another. The radially inner housing area and the radially outer housing area are firmly connected to one another via the struts extending in the radial direction through the flow cross-section. Such an intermediate housing is usually arranged between a low pressure compressor and a high pressure compressor. Oil is guided through one of the struts, which in the installed position of the turbo machine through an area of the flow cross-section lying below a horizontal symmetry plane of the turbo machine, from the radially inner engine area into the radially outer engine area due to the gravity acting on the oil.

A gas turbine engine of an aircraft with at least one inner engine area and with at least one outer engine area which at least regionally limit a flow cross section for air through the gas turbine engine is known from US 2018/0306042 A1. The inner engine area and the outer engine area are connected to one another via struts which extend radially through the flow cross section and are spaced apart from one another in the circumferential direction of the flow cross section. A strut running through the flow cross-section in the installed position of the gas turbine engine above a horizontal symmetry plane of the gas turbine engine is designed with an oil line through which oil from the radially inner engine area radially in the direction of the outer engine area and inside the strut like the back in the direction of the inner engine area can be guided in order to cool the oil guided through the strut by means of the air stream flowing around the strut.

In addition, US 2011/0268562 A1 describes a gas turbine engine that includes a flow cross section for air. An outer engine area and a radially inner engine area limit the flow cross-section for air. The two engine areas are connected to one another via struts extending radially through the flow cross-section. Through at least one of the struts, oil can be guided through the flow cross-section starting from the outer engine area in the direction of the inner engine area and in the strut back in the direction of the outer engine area in order to cool the oil guided through the strut accordingly by means of the air stream flowing around the strut. The present disclosure is based on the object of providing a gas turbine engine which can be manufactured as easily as possible, in which the temperature of the oil can be controlled with little structural effort and which can be operated with a high degree of efficiency.

This object is achieved with a gas turbine engine with the features of claim 1.

According to a first aspect, a gas turbine engine of an aircraft is provided with at least one inner engine area and with at least one outer engine area. The engine areas limit a flow cross-section for air through the gas turbine engine at least in certain areas. Furthermore, the gas turbine engine comprises at least one device which is arranged in the inner or outer area of the engine and can be acted upon with oil. The inner engine area and the outer engine area are in operative connection with one another via struts which run radially through the flow cross-section and are spaced apart from one another in the circumferential direction of the flow cross-section.

It can be provided that oil from a return of the device, in the area of which the operating temperature is greater than the temperature of the air that can be guided through the flow cross-section, to cool the oil through at least one of the struts from the inner engine area into the outer engine area and / or can be guided from the outer engine area into the inner engine area.

The heated oil can optionally be tempered or cooled without a heat exchanger to be arranged in the flow cross-section, since the oil is passed through the at least one strut radially through the flow cross-section in the direction of the inner or outer engine area. In doing so, the oil is in the area the strut is cooled by the air flowing around the strut, which has a lower temperature level than the oil that is passed through the strut.

Depending on the application at hand and the arrangement as well as the course of the strut in the circumferential direction of the engine areas, there is the possibility that the oil with the help of a corresponding pressurization against the attacking gravity or additionally supporting the attacking force of gravity from the inner engine area into the outer drive plant area and / or from the outer engine area into the inner engine area is performed.

It can also be provided that the oil is guided solely by gravity acting on the oil through the at least one strut from the inner engine area into the outer engine area and / or from the outer engine area into the inner engine area.

The gas turbine engine according to the present disclosure offers the advantage that the efficiency of a known gas turbine engine is not impaired despite a significant increase in the cooling capacity. This is achieved in that the oil is cooled in the area of already existing components of a gas turbine engine, namely in the area of struts extending radially through the flow cross-section.

Also, heat exchangers or oil coolers already known from the prior art, which are arranged on the outside of the inner engine area and / or on the inner side of the outer engine area and impair the air flow in the flow cross-section, can no longer be required or are of smaller dimensions . Then there is, for example, the possibility of improving the aerodynamic efficiency of a known gas turbine engine with the same cooling capacity. In a further embodiment of the gas turbine engine according to the present disclosure, oil from a return of the device is at least in the area of one of the struts which, in the installed position of the gas turbine engine, runs through an area of the flow cross section lying below or above a horizontal symmetry plane of the gas turbine engine the flow cross-section from the inner engine area into the outer engine area or from the outer engine area into the inner engine area can be guided.

In addition, the oil in the outer engine area or in the inner engine area can be guided in the circumferential direction of the gas turbine engine to at least one further strut, which runs through an area of the flow cross-section above or below the horizontal plane of symmetry of the gas turbine engine and through which the oil flows through the Flow cross-section can be introduced from the outer engine area into the inner engine area or from the inner engine area into the outer engine area.

It can additionally be provided that the oil is guided between the struts at least one line running in the circumferential direction. The line can abut or border on a wall area of the inner engine area that delimits the flow cross-section radially on the inside, or with a wall area of the outer engine area that delimits the flow cross-section radially on the outside. In this way, the oil can be cooled by the volume of air flowing through the flow cross-section while flowing through the line. Furthermore, there is the possibility that the at least one line is made in one piece with the wall of the inner engine area or with the outer engine area.

In the present case, a horizontal symmetry plane of the gas turbine engine is understood to mean a plane in which a main axis of the gas turbine engine, which extends in the axial direction of the gas turbine engine, is located divides the gas turbine engine into an upper and a lower half. Starting from a circumferential subdivision of the gas turbine engine into twelve equal parts, which corresponds to a subdivision of a dial of an analog clock, the horizontal symmetry plane of the gas turbine engine runs through the main axis and additionally through the 3 o'clock position and 9 o'clock -Position.

In addition, it can be provided that the oil flowing into the inner engine area through the strut and / or the further strut is introduced into the return of the device. There is thus the possibility of using already available oil lines in gas turbine engines and performing existing gas turbine engine systems with little structural measures according to the present disclosure in order to improve a cooling capacity for oil ei nes oil circuit of a gas turbine engine.

In further embodiments of the gas turbine engine according to the present disclosure, oil can be guided in the area of an additional strut from the outer or inner engine area in the direction of the inner or outer engine area up to a defined area. The defined area can have a defined distance in the radial direction from the outer or inner engine area. The oil in the additional strut can then be reintroduced into the outer or inner engine area from the defined area of the additional strut. By means of this embodiment of the gas turbine engine according to the present disclosure, the cooling performance of the gas turbine engine can be improved or increased in a structurally simple manner in comparison to known gas turbine engines without impairing or worsening the aerodynamic efficiency of the gas turbine engine.

The oil is in further embodiments of the gas turbine engine according to the present disclosure downstream of the strut and upstream of the wide Ren strut and / or in an area in the inner engine area between the Return of the device and the strut initiated into the additional strut. This ensures that the oil in the area of the additional strut is tempered or cooled by the air volume flow flowing onto the additional strut, without impairing the aerodynamic efficiency of the gas turbine engine according to the present disclosure in comparison to the gas turbine engines known from the prior art becomes.

If an oil collection area is provided in the inner or outer engine area downstream of the device and upstream of the strut and / or upstream of the further additional strut, a continuous oil volume flow through the strut, the further strut and / or the additional strut is easy guaranteed. Furthermore, oil from other hydraulic consumers of the gas turbine engine according to the present disclosure can initially be introduced into the oil collection area and can be tempered or cooled in the area of the strut, the further strut and / or the additional strut.

In further embodiments of the gas turbine engine according to the present disclosure, at least one return pump can be provided between the device and the strut and / or the additional strut or between the oil collection area and the strut and / or the additional strut. By means of such a return pump, oil can be sucked out of the device and a required delivery pressure for a continuous oil flow through the strut and / or the additional strut and for a desired cooling capacity can be made available.

The oil flow and thus the desired cooling capacity for the oil can also be implemented or supported by at least one pump arranged in the outer or inner area of the engine. It can be provided that the pump is arranged in the flow path of the oil between the strut and the additional strut and / or between the strut and the further strut in the outer or in the engine area. In order to be able to achieve the highest possible temperature control of the gas turbine engine according to the present disclosure, at least one of the struts can have at least one oil guide area extending inside the strut, which extends inside the strut over the entire inner cross section of the strut. This ensures that in the area of the strut, which then represents a heat exchanger for the oil, the largest possible heat exchange surface is present between the oil and the air flowing around the strut.

If inside one of the struts described above, in addition to the oil guide area, other supply lines, such as electrical lines, air lines or the like, or mechanical operative connections, such as shafts or the like, are routed, it can be provided that the oil guide area is only rich via one Part of the cross section of the strut extends. Then it can also be provided that the oil guide area includes the at least one supply line and / or mechanical operative connection on the circumferential side.

In a further embodiment of the gas turbine engine according to the present disclosure, a high cooling capacity for the oil is achieved in a structurally simple manner in that the oil guide area is delimited by the outer wall of the at least one strut. The air volume flow in the flow cross-section then flows directly into the oil guide area.

If the oil guiding area of the at least one strut has wall areas protruding from the outer wall of the strut into the oil guiding area, the oil flowing through the at least one strut is held or held on the inner side of the outer wall area of the at least one strut with little constructive effort guided along and a high heat exchange rate guaranteed. The oil guide area of the at least one strut comprises in a wide Ren embodiment of the gas turbine engine according to the present disclosure in each case a circumferential gap which is delimited by an inner wall spaced apart from the outer wall of the strut and the outer wall. This achieves in a structurally simple manner that the oil flows inside the at least one strut on the inside of the outer wall of the strut and the largest possible heat exchange surface is present between the oil in the strut and the air volume flow outside the strut, which enables a high cooling capacity for the oil in the area of the strut.

The best possible distribution of the oil flowing through the at least one strut is achieved in a further embodiment of the gas turbine engine according to the present invention in that the circumferential gap of the oil guide area of the at least one strut is channeled at least in some areas through bulkheads in the circumferential direction of the at least one strut like gap sections is divided. It can be provided that the bulkheads each extend between the outer wall and the inner wall of the at least one strut. This embodiment of the gas turbine engine thus comprises several circumferentially adjacent oil guide areas or oil channels that ensure the best possible distribution of the oil flow in the circumferential direction of the at least one strut on the inside of the outer wall. This enables a high cooling capacity.

In order to be able to distribute the oil as evenly as possible over the outer circumference of the at least one strut on the inside of the outer wall, the oil can be introduced into the strut via at least one nozzle. There is the possibility that the oil is sprayed or injected into the at least one strut. Furthermore, there is the possibility that the oil against the gravity acting on the oil, starting from the radially outer engine area in the direction of the radially inner engine area or from the radially inner engine area in the direction of the radially outer engine area in the radial direction into the interior of a strut up to a defined height of the strut is injected against the inner side of the outer wall of the strut. Then the oil is guided by gravity on the inner side of the outer wall of the strut back in the direction of the radially inner engine area or in the direction of the radially outer engine area and is cooled accordingly in the interior of the strut.

The device of the gas turbine engine that can be acted upon by oil can be designed, for example, as a storage chamber. Furthermore, there is the possibility that the oil guided through the further strut into the inner engine area is introduced into an inner area of the bearing chamber which is arranged above the horizontal plane of symmetry of the bearing chamber. It can be provided that the oil is introduced into the bearing chamber in such a way that the oil flows along an inner side of the bearing chamber in the direction of an extraction point for the oil from the bearing chamber located below the horizontal plane of symmetry. It is thereby achieved in a structurally simple manner that the oil can also give off heat to the surroundings of the bearing chamber in the area of the inside of the bearing chamber and is additionally temperature-controlled.

If a flow limiter is provided between the device and at least one of the struts, the cooling capacity of the gas turbine engine can be limited or adjusted in a simple manner.

It will be understood by those skilled in the art that a feature or parameter described in relation to any of the above aspects can be applied to any other aspect, provided that they are not mutually exclusive. Furthermore, any feature or any Parameters described herein can be applied in any aspect and / or combined with any other feature or parameter described herein, unless they are mutually exclusive.

Embodiments will now be described by way of example with reference to the figures, the same reference numerals being used in the description of the various embodiments for the sake of clarity for structural and functionally identical components.

It shows:

Fig. 1 is a highly schematic longitudinal sectional view of a gas turbine engine;

Fig. 2 is a simplified front view of an intermediate housing of the

Gas turbine engine according to FIG. 1 in isolation;

3 shows a block diagram of an oil circuit of the gas turbine engine according to FIG. 1; and

4 to 6 each show a greatly simplified sectional view of a

Strut along a section line IV-IV shown in more detail in FIG. 2.

1 shows a gas turbine engine 1, preferably for an aircraft, in a schematic longitudinal sectional view. The gas turbine engine 1 is formed with a bypass duct 2 and with an inlet area 3, with a fan 4 connected to the inlet area 3 downstream in a manner known per se. Downstream of the fan 4, the fluid flow in the gas turbine engine 1 is divided into a secondary flow A and a core flow B. The bypass flow A flows through the bypass duct 2, while the core flow B flows into an engine core 5 flows. The engine core 5 is carried out in a manner known per se with a Ver sealing device 6, a burner 7 and a turbine device 8.

In the present case, the gas turbine engine 1 has two shafts with a first shaft 9 representing a low pressure wave and a second shaft 10 representing a high pressure wave. The low-pressure shaft 9 and the high-pressure shaft 10 are each rotatably mounted about a central axis or central axis 19. The low-pressure shaft 9 is non-rotatably connected to the fan 4 and, when the gas turbine engine 1 is in operation, rotates at a lower speed around the central axis 19 than the high-pressure shaft 10. To support the shafts 9, 10 with one another and with respect to a housing 11 of the gas turbine engine 1, there are several bearings

14, 15, 16, 17A, 17B are provided. The bearings 14, each designed as a roller bearing,

15, 16 are present in a front bearing chamber 12 in the axial direction X of the gas turbine engine 1, while the bearings 17A and 17B also run as roller bearings in a rear bearing chamber 13 in the axial direction X of the gas turbine engine 1.

In addition, the housing 11 of the gas turbine engine 1 comprises an intermediate housing 18, shown in more detail in FIG. 2. Furthermore, the gas turbine engine 1 has several housing parts that adjoin one another in the axial direction X of the gas turbine engine 1 and are connected to one another. The upstream angeord designated inlet area 3 is in this case formed by an inlet housing, to which the fan 5 is connected downstream in the assembled state of the gas turbine engine 1, a fan housing containing the fan. The intermediate housing 18 connects downstream of the fan housing, to which a sheath current housing is connected in the present case.

In an alternative embodiment to this, the jet engine can be constructed differently with regard to the number and arrangement of the housing parts. For example, fewer or more housing areas than described above can be provided in the axial direction of the jet engine. In addition, there is also the Possibility of designing individual housing parts described above in the axial and / or radial direction of the jet engine in several parts.

The gas turbine engine 1 can be connected to an aircraft via the intermediate housing 18, so that loads occurring during the operation of the gas turbine engine 1 are guided via the intermediate housing 18 to a support strut of the gas turbine engine 1, not shown in detail, which can be brought into operative connection with the intermediate housing 18 a structure of the aircraft can be derived. Such a gas turbine engine 1 is also referred to as a case-mounted engine.

In the following, the intermediate housing 18 of the gas turbine engine 1 is described in more detail, which extends from the central axis 19 of the gas turbine engine 1 or the intermediate housing 18 outward in the radial direction Y and from which in the radial direction Y at least one area of the core flow duct and an area of the bypass duct 2 is limited.

In the present case, the intermediate housing 18 comprises two annular housing areas 20, 21, which are firmly connected to one another via struts 22 which run radially between the housing areas 20, 21 and are spaced from one another in the circumferential direction U of the gas turbine engine 1. From mutually facing surfaces 23, 24 of the two housing parts 20, 21, part of the Nebenstromka channel 2 is limited in the radial direction Y in each case. The housing parts 20, 21 are connected to one another in the exemplary embodiment shown via eight struts 22, the struts 22 being connected at the ends in the area of the surfaces 23 and 24 with the housings 20, 21.

The circumferentially in particular evenly distributed struts 22, which are also referred to as struts, are aerodynamically shaped both in the area of a front side 25 facing the fluid flow or air flow A in the secondary flow channel 2 and in the area of a rear side 26 and serve in addition to the flow guidance in the flow cross section 2 in particular for the transfer of loads the core area of the gas turbine engine 1 radially outward. To implement service lines from an engine area 27 located radially inside the radially inner housing area 21 to an engine area 28 located radially outside the radially outer housing part 20 and / or for weight reduction, there is the possibility that one, several or all of the struts 22 are hollow are executed.

Fig. 2 shows the intermediate housing 18 in the installation position of the gas turbine engine 1 on an aircraft or aircraft. A horizontal symmetry plane HE of the gas turbine engine 1 and thus also of the intermediate housing 18 ver runs through two essentially horizontally aligned struts 22A and 22B as well as through the central axis 19. The horizontal symmetry plane HE thus divides the intermediate housing 18 into an upper one Part and into a lower part. Within the radially inner housing area 21, the front bearing chamber 12 is presently arranged, which represents a device arranged in the radially inner engine area 27 and which is acted upon with oil during operation of the gas turbine engine 1.

The oil supplied to the front bearing chamber 12 is guided by a return 31 of the bearing chamber 12, shown in more detail in FIG. 3, in the area of a lower strut 22C from the inner engine area 27 radially outward in the direction of the radially outer engine area 28. In the installation position shown in FIG. 2, the lower strut 22C runs through the area of the flow cross-section or the side stream channel 2 located below the horizontal plane of symmetry HE. The lower strut 22C is circumferentially in a so-called 6 in FIG Clock position of the gas turbine engine 1 is arranged and thus runs radially downward through the Ne benstromkanal 2 perpendicular to the horizontal symmetry plane HE.

The oil, which is also guided through the strut 22C by the force of gravity acting on the oil, is initially stored in an oil tank 29 downstream of the lower strut 22C collected, which is arranged in the radially outer engine area 28. From the oil tank 29, the oil in the radially outer engine area 28 is guided in the circumferential direction U to a further strut 22D. The further strut 22D is arranged in the installation position of the gas turbine engine 1 shown in FIG. 2 in a region of the flow cross section 2 lying above the horizontal plane of symmetry HE. The further or upper strut 22D lies in a so-called 12 o'clock position and is arranged in the bypass duct 2, pivoted by 180 ° in the circumferential direction U of the gas turbine engine 1 relative to the lower strut 22C. The oil supplied to the upper strut 22D therefore also flows out of the radially outer engine area 28 in the direction of the radial inner engine area 27 due to the force of gravity acting on the oil.

The oil in the area of the upper strut 22D is cooled by the bypass flow A or by the air volume flow guided through the bypass flow duct 2 and tempered to the desired extent with little structural effort.

If the additional cooling capability or cooling capacity created in the area of the upper strut 22D to control the temperature of the oil of the gas turbine engine 1 should not be sufficient, it can be provided that the oil removed from the return 31 of the front bearing chamber 12 from the radially inner engine area 27 is introduced into a further strut 22E in the direction of the radially outer engine area 28. The further strut 22E is also arranged in the area of the bypass duct 2 lying below the horizontal plane of symmetry HE. It is thereby achieved that the oil introduced into the lateral lower strut 22E flows radially in the direction of the radially outer engine area 28 due to the force of gravity. In addition, an impulse of such a kind is impressed on the oil via a corresponding device, such as a feed pump or the like, before it enters the lateral lower strut 22E that the oil in the interior of the lateral lower strut 22E flows from one of the radially outer engine area 28 facing end of the lateral lower strut 22E flows back into the radially inner engine area 27 and then into the lower strut 22C is initiated. In this way, the oil removed from the bearing chamber 12 in the area of the lateral lower strut 22E is also cooled by the secondary flow A, which flows against the outside of the lateral lower strut 22E.

In order to further increase the cooling capacity for the oil in the gas turbine engine 1 or in the area of the intermediate housing 18, it is provided in a further possible embodiment of the gas turbine engine 1 that the oil from the oil tank 29 or from the lower strut 22C into the radially outer engine bay rich 28 inflowing oil is first introduced into an additional strut 22F before it is introduced into the upper strut 22D.

As an alternative to this, it can also be provided that oil is introduced into the additional star 22F independently of the guidance of the oil between the lower strut 22C and the upper strut 22D.

The additional strut 22F is arranged in the circumferential flow path of the oil between the lower strut 22C and the upper strut 22D upstream of the upper strut 22D and above the horizontal plane of symmetry HE in the bypass duct 2. In this case, the oil is first guided from the radially outer engine area 28 through the interior of the lateral upper strut 22F radially inward in the direction of the radially inner engine area 27. As soon as the oil inside the additional strut 22F has reached the end of the additional strut 22F facing the radially inner engine area 27, the oil in the lateral upper strut 22F flows back in the direction of the radially outer engine area 28 and becomes the mouth area of the upper one Strut 22D out. The oil is also cooled in the area of the lateral upper strut 22F by the secondary stream A flowing around the outside of the lateral upper strut 22F.

The oil is in the interior of the lateral lower strut 22E and also in the interior of the lateral upper strut 22F each up to a defined area of the Struts 22E and 22F out. The defined areas each have a defined distance from the inner engine area 27 and from the outer engine area 28 in the radial direction Y of the intermediate housing 18. The distances in the embodiment of the gas turbine engine 1 shown in FIG. 2 are each the same size and essentially correspond to the entire radial distance between the outer side 24 of the radially inner housing area 21 and the inner side 23 of the radially outer housing area 20.

Fig. 3 shows a greatly simplified block diagram of an oil circuit 30 of the gas turbine engine 1 according to FIG. 1. The illustration according to FIG. 3 accordingly, the oil in the area of the return 31 from the front bearing chamber 12 is introduced into a return line RL1. In the present case, the return line RL1 runs in the manner described above only through the lower strut 22C. The return line RL1 is connected to a suction side of a return pump 32, via which the oil is sucked out of the front bearing chamber 12. The return pump 32 conveys the oil into the oil tank 29. In addition, the return pump 32, as shown in FIG. 3, can also be connected to a return 33 of the rear bearing chamber 13 and also suck oil from the rear bearing chamber 13.

A feed pump 34 conveys oil from the oil tank 29 in the direction of a filter 35, in the area of which the oil removed from the oil tank 29 is filtered. In parallel with the oil filter 35, a bypass valve 36 is provided via which the oil delivered by the delivery pump 34 can be guided past the oil filter 35 if the pressure loss in the area of the oil filter 35 is too high. In addition, a differential pressure transducer 36B is provided in an oil path 36A parallel to the oil filter 35, by means of which a pressure difference between the pressure at the inlet of the oil filter 35 and at the outlet of the oil filter 35 can be determined. The bypass valve 36 can be actuated via the specific pressure difference.

Downstream of the oil filter 35 and the bypass valve 36A, the oil is guided in the direction of a heat exchanger 37, in the area of which the oil is fueled of the aircraft is tempered or cooled. The fuel is conducted through the heat exchanger 37 via a fuel line T1. Downstream of the heat exchanger 37, the oil is guided in the direction of the two storage chambers 12 and 13 and in the direction of an auxiliary device transmission 38A of the gas turbine engine 1 in order to be able to supply these areas of the gas turbine engine to the desired extent with oil.

Air laden with oil is guided out of the two storage chambers 12 and 13 via vent lines V12 and V13 in the direction of an oil separator 38, which is also referred to as a breather. In the area of the oil separator 38, the oil is separated from the air laden with oil in a manner known per se and is sucked in by the return pump 32 and introduced into the oil tank 29. The air cleaned of oil is released from the oil separator 38 to the environment of the gas turbine engine 1. A line L1 runs between the heat exchanger 37 and the two storage chambers 12. The rear storage chamber 13 is connected to the return pump 32 via a return line RL2.

In the flow path of the oil between the oil filter 35 and the Wärmetau shear 37, another line L2 branches off, via which the oil removed from the oil tank 29 and filtered in the oil filter 35 in the outer engine area 28 is guided to the top side to the upper strut 22D and through the upper one Strut 22D is introduced radially inward into the inner engine area 27. From there, the oil passed through the upper strut 22D is introduced into the front bearing chamber 12. Furthermore, a flow limiter 50 is provided in the further line L2 with a throttling effect that can preferably be varied, with the result that the cooling capacity of the gas turbine engine 1 can be limited or adjusted.

The oil is fed into the interior of the front bearing chamber 12 in such a way that the oil on the inside of the bearing chamber wall comes from an area of the bearing chamber 12 located above the horizontal plane of symmetry HE radially downward in the direction of the return 31 of the front bearing chamber 12th flows. It is thereby achieved that the oil guided through the bearing chamber 12 is further tempered or cooled in the area of the outer wall of the bearing chamber 12.

It can be provided that the inside of the outer wall of the front bearing chamber 12 is designed with oil guide grooves or the like, into which the oil introduced into the bearing chamber 12 is guided to a defined extent through the bearing chamber 12 in the direction of the return 31.

4 to 6 each show a cross-sectional view of various embodiments of the upper strut 22D, which is designed to be hollow on the inside, along a section line IV-IV shown in more detail in FIG. 2. It is pointed out that each of the struts 22 of the intermediate housing 18 can be designed in the manner described below.

In the embodiment of the upper strut 22D shown in FIG. 4, an oil guide region 40 of the upper strut 22D extends over the entire cross section of the upper strut 22D. So that the oil introduced into the upper strut 22D flows to the desired extent over the entire inner surface of the inner side 41A of the outer wall 41 of the upper strut 22D from the radially outer engine area 27 in the direction of the radially inner engine area 28, the oil guide area 40 comprises Upper strut 22D wall regions 42 protruding from the outer wall 41 into the oil guide region 40.

In the exemplary embodiment of the upper strut 22D shown in FIG. 5, the oil guide region 40 of the upper strut 22D comprises a circumferential gap 43, which is spaced from an inner wall 41 or the inner side 41A of the outer wall 41 of the upper strut 22D Wall 44 is limited. The circumferential gap 43 of the oil guide area 40 of the upper strut 22D is in the exemplary embodiment shown in FIG. The bulkhead walls 45 each extend between the outer wall 41 and the inner wall 44 of the upper strut 22D.

There is also the possibility of the oil guide area or the oil guide areas inside the strut or inside the struts as complex, closed passages that can be produced, for example, by means of casting or by means of a generative manufacturing process such as 3-D printing or the like, to be provided. Since the flow direction is defined by the applied delivery pressure of the oil in closed structures, any flow direction in the interior of the strut or the struts can be implemented.

Depending on the particular application, there is also the possibility that oil is introduced into the upper strut 22D via at least one nozzle. It can be provided that the oil is either sprayed in or injected in order to be able to distribute the oil as evenly as possible over the entire circumferential area of the inner side 41A of the outer wall 41 through the upper strut 22D and to ensure the greatest possible cooling capacity.

It is of course at the discretion of the person skilled in the art to execute the further struts 22C, 22E, 22F in the scopes described in more detail for FIGS. 4 to 6 in order to be able to provide the greatest possible cooling capacity in the area of the intermediate housing 18.

Furthermore, there is also the possibility, in addition or as an alternative to the struts 22 arranged in the bypass duct 2, to also design a housing of an aircraft engine according to the present disclosure, the struts of which run through the flow cross-section of the core flow B in order to allow oil to flow into the area through the struts To cool or temper the core flow. Reference list

Gas turbine engine

Sidestream channel

Inlet area

Wind players

Engine core

Compressor device

burner

Turbine device first shaft, low pressure shaft second shaft, high pressure turbine housing front bearing chamber rear bearing chamber

warehouse

Camp A, 17B camp

Intermediate housing central axis, central axis radially outer housing area radially inner housing area Strut A, 22B Strut C lower strut D upper strut E further strut F additional strut

Inside of the housing area 20, outside of the housing area 21 25 Front of the strut

26 Back of the strut

27 radially inner engine area

28 radially outer engine area

29 oil tank

30 oil circuit

31 Return of the front storage chamber 12

32 return pump

33 Return of the rear storage chamber 13

34 Feed pump

35 oil filters

36 Bypass valve 36A oil path

36 B differential pressure transducer

37 heat exchanger

38 Oil separator, Breather 38A auxiliary equipment gear

39 Differential pressure transducers

40 Oil guide area

41 outer wall of the upper strut 22D 41 A inner side of the outer wall of the upper strut 22D

42 Wall area

43 circumferential gap

44 inner wall

45 bulkhead

46 gap section 50 flow limiter A secondary flow B core flow

HE Horizontal symmetry plane

management RL1, RL2 return line U circumferential direction of the gas turbine engine

V12, V13 vent line

T1 fuel line

X axial direction of the gas turbine engine

Y radial direction of the gas turbine engine

Claims

1. Gas turbine engine (1) of an aircraft with at least one inner engine area (27) and with at least one outer engine area (28), which at least regionally limit a flow cross-section (2) for air through the gas turbine engine (1), and with at least one inside The engine area (27) and / or in the outer engine area (28) arranged device (12) which can be acted upon by oil, the inner engine area (27) and the outer engine area (28) extending radially through the flow cross-section (2) and in Circumferential direction (U) of the flow cross-section (2) spaced struts (22, 22A to 22F) are in operative connection with each other, and oil from a return (31) of the device (12), in the area of which the operating temperature is higher than the Temperature of the air, which can be guided through the flow cross-section (2), for cooling the oil through at least one of the struts (22) from the inner engine s area (27) can be guided into the outer engine area (28) and / or from the outer engine area (28) into the inner engine area (27).

2. Gas turbine engine according to claim 1, characterized in that we at least in the area of one of the struts (22C, 22D), which in the installed position of the gas turbine engine (1) by a below or above a horizontal plane of symmetry (HE) of the gas turbine engine (1 ) lying area of the flow cross section (2) runs through the flow cross section (2) from the inner or the outer engine area (27 or 28) in the outer or inner engine area (28 or 27) and in the outer or inner engine area (27 o - The 28) can be guided in the circumferential direction (U) to at least one further strut (22D) which runs through an area of the flow cross section (2) lying above or below the horizontal symmetry plane (HE) of the gas turbine engine (1) and through which the oil through the Flow cross-section (2) from the outer or inner engine area (28 or 27) can be guided into the inner or outer engine area (27 or 28).

3. Gas turbine engine according to claim 1, characterized in that the oil can be fed to the return (31) of the device (12) downstream of the strut (22C) and / or the further strut (22D) in the inner engine area (27).

4. Gas turbine engine according to claim 2 or 3, characterized in that oil in the area of at least one additional strut (22E) from the outer or inner engine area (28) in the direction of the inner or outer engine area (27) up to a defined area which in the radial direction (Y) has a defined distance from the outer or inner engine area (28), can be guided and in the additional strut (22E) from the defined area of the additional strut (22E) back into the outer or inner engine area (28 ) can be initiated.

5. Gas turbine engine according to claim 3, characterized in that oil downstream of the strut (22C) and upstream of the further strut (22D) and / or in an area in the inner engine area (27) between the return (31) of the device (12) and the strut (22C) can be guided into the additional strut (22F).

6. Gas turbine engine according to claim 5, characterized in that an oil collecting area is provided in the engine area (27) downstream of the device (12) and upstream of the strut (22C), the further strut and / or upstream of the additional strut (22F).

7. Gas turbine engine according to claim 5 or 6, characterized in that in the flow path of the oil between the device (12) and the strut (22C) and / or the additional strut (22F) is provided with at least one return pump (32).

8. Gas turbine engine according to one of claims 5 to 7, characterized in that in the flow path of the oil between the strut (22C) and the additional strut (22E) and / or between the strut (22C) and the wide Ren strut (22D) and / or between the additional strut (22E) and the further strut (22D) at least one pump (34) arranged in the outer and / or inner engine area (28) is provided.

9. Gas turbine engine according to one of claims 1 to 8, characterized in that at least one of the struts (22D) has at least one in the interior Ren of the strut (22D) extending oil guide region (40), which is in each case in the interior of the strut (22D) extends over the entire inner cross-section of the strut (22D).

10. Gas turbine engine according to claim 9, characterized in that the oil guide region (40) is bounded by the outer wall (41) of the at least one strut (22D).

11. Gas turbine engine according to claim 9 or 10, characterized in that the oil guide area (40) of the at least one strut (22D) from the outer wall (41) of the strut (22D) into the oil guide area (40) in front of projecting wall areas (42) .

12. Gas turbine engine according to one of claims 9 to 11, characterized in that the oil guide region (40) of the at least one strut (22D) each comprises a circumferential gap (43) which extends from the outer wall (41) of the strut (22D) spaced inner wall (44) is limited.

13. Gas turbine engine according to claim 12, characterized in that the circumferential gap (43) of the oil guide area (40) of the at least one strut (22D) at least partially in each case by bulkheads (45) in the circumferential direction of the at least one strut (22D) in channel-like Spaltab Sections (46) is divided, the bulkheads (45) each extending between the outer wall (40) and the inner wall (44) of the at least one strut (22D).

14. Gas turbine engine according to one of claims 1 to 13, characterized in that the oil can be introduced into at least one of the struts (22) via at least one nozzle.

15. Gas turbine engine according to one of claims 1 to 14, characterized in that the device (12) is designed as a storage chamber and the through the further strut (22D) in the inner engine area (27) led oil into an inner area of the Bearing chamber (12), which is arranged above the horizontal plane of symmetry (HE) of the bearing chamber (12), is initiated in such a way that the oil along an inside of the bearing chamber (12) in the direction of a below the horizontal plane of symmetry (HE) are the extraction points for the oil flowing out of the storage chamber (12).