DE102019135339A1 - Aircraft gas turbine engine - Google Patents

Abstract

A gas turbine engine (1) of an aircraft is described with an inner engine area (27) and an outer engine area (28) which limit a flow cross-section (2) and are in operative connection with one another via struts (22, 22A to 22F). Oil is from a return (31) of the device (12), in the area of which the operating temperature is higher than the temperature of the air that can be guided through the flow cross-section (2), for cooling the oil through at least one of the struts (22C, 22D , 22E, 22F) from the inner engine area (27) into the outer engine area (28) and / or from the outer engine area (28) into the inner engine area (27).

Description

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 the WO 2019/086 065 A1 a fluid flow machine is known which comprises an intermediate channel or a flow cross section for air. The intermediate duct is delimited 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 has a minimal wall thickness in order to be able to guide supply lines, such as oil lines, through the interior of the strut and thus through the flow cross-section.

Furthermore, the FR 3 030 627 B1 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 devices of the inner engine area with devices of the outer engine area. 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 from the radially inner engine area into the radially outer engine area due to the force of gravity acting on the oil through one of the struts, which in the installed position of the turbomachine runs through an area of the flow cross-section below a horizontal symmetry plane of the turbomachine.

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 delimit a flow cross section for air through the gas turbine engine, is from FIG US 2018/0306042 A1 known. 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. 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 is radially in the direction of the outer engine area and within the strut back again 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, the US 2011/0268562 A1 a gas turbine engine is described which 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 again 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 that is as simple as possible to manufacture, 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 engine area 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 higher than the temperature of the air that can be guided through the flow cross-section, for cooling the oil through at least one of the struts from the inner engine area to the outer one The 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. The oil in the area of 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 particular application 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 engine area and / or is guided from the outer engine area into the inner engine area.

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, may no longer be required or have 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, through the Flow cross-section can be guided from the inner engine area into the outer engine area or from the outer engine area into the inner engine area.

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 lying above or below the horizontal symmetry plane of the gas turbine engine and through which the oil flows through the flow cross section the outer engine area can be introduced 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 adjoin a wall area of the inner engine area which delimits the flow cross section radially on the inside, or a wall area of the outer engine area which delimits the flow cross section radially on the outside. In this way, the oil can be cooled by the air volume flow flowing through the flow cross section while it is 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 running in the axial direction of the gas turbine engine lies and which divides the gas turbine engine into an upper and a lower half. Based on 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 as well as through the 3 o'clock position and the 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 flow of the facility. This makes it possible to use oil lines that are often already available in gas turbine engines and to implement existing gas turbine engine systems with few structural measures in accordance with the present disclosure in order to improve a cooling capacity for oil in an 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.

In further embodiments of the gas turbine engine according to the present disclosure, the oil is introduced into the additional strut downstream of the strut and upstream of the further strut and / or in an area in the inner engine area between the return of the device and the strut. This ensures that the oil in the area of the additional strut is tempered or cooled by the air volume flow approaching the additional strut, without the aerodynamic efficiency of the gas turbine engine according to the present disclosure being impaired in comparison to the gas turbine engines known from the prior art .

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 can be ensured in a simple manner. 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 drawn off from the device and a required delivery pressure can be made available for a continuous oil flow through the strut and / or the additional strut and for a desired cooling capacity.

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 inner engine area.

In order to be able to achieve the highest possible temperature control performance of the gas turbine engine according to the present disclosure, at least one of the struts can have at least one oil guide area running 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, in addition to the oil guide area, further supply lines, such as electrical lines, air lines or the like, or mechanical operative connections, such as shafts or the like, are routed inside one of the struts described above, it can be provided that the oil guide area extends only over 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 guided in the flow cross-section then flows directly into the oil guide area.

If the oil guide area of the at least one strut points away from the outer wall of the strut wall areas protruding into the oil guide area, the oil flowing through the at least one strut is held on the inner side of the outer wall area of the at least one strut or guided along it with little structural effort and a high heat exchange performance is ensured.

In a further embodiment of the gas turbine engine according to the present disclosure, the oil guiding area of the at least one strut comprises 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. It is thereby achieved in a structurally simple manner that the oil inside the at least one strut flows along 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 enables 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 at least partially subdivided into channel-like gap sections by bulkheads in the circumferential direction of the at least one strut is. 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 oil guide areas or oil channels adjoining one another in the circumferential direction, which 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, against the force of 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 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 storage chamber in such a way that the oil flows along an inside of the storage chamber in the direction of an extraction point for the oil from the storage 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 parameter described here can be applied to any aspect and / or combined with any other feature or parameter described here, insofar as they are compatible not 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.

• 1 eine stark schematisierte Längsschnittansicht eines Gasturbinentriebwerkes;
• 2 eine vereinfachte Vorderansicht eines Zwischengehäuses des Gasturbinentriebwerkes gemäß 1 in Alleinstellung;
• 3 ein Blockschaltbild eines Ölkreislaufes des Gasturbinentriebwerkes gemäß 1; und
• 4 bis 6 jeweils eine stark vereinfachte Schnittansicht einer Strebe entlang einer in 2 näher gezeigten Schnittlinie IV-IV.

It shows:

• 1 a highly schematic longitudinal sectional view of a gas turbine engine;
• 2 a simplified front view of an intermediate housing of the gas turbine engine according to FIG 1 in isolation;
• 3 a block diagram of an oil circuit of the gas turbine engine according to 1 ; and
• 4th to 6th each a greatly simplified sectional view of a strut along an in 2 Section line IV-IV shown in more detail.

1 shows a gas turbine engine 1 , preferably for an aircraft, in a schematic longitudinal sectional view. The gas turbine engine 1 is with a bypass duct 2 and with an inlet area 3 formed, being attached to the inlet area 3 downstream a horn 4th connects in a known manner. Downstream of the horn 4th the fluid flow divides in the gas turbine engine 1 in a side stream A. and a core stream B. on. The tributary A. flows through the bypass duct 2 during the core stream B. into an engine core 5 flows. The engine core 5 is in a manner known per se with a compressor device 6th , a burner 7th and a turbine device 8th executed.

The gas turbine engine 1 is in the present case two-shaft with a first shaft representing a low-pressure shaft 9 and a second wave representing a high pressure wave 10 executed. The low pressure wave 9 and the high pressure wave 10 are each around a central axis or central axis 19th rotatably mounted. The low pressure wave 9 rotates with the horn 4th connected and rotates during operation of the gas turbine engine 1 with a lower speed around the central axis 19th than the high pressure wave 10 . For storing the shafts 9 , 10 among each other and across from a housing 11 of the gas turbine engine 1 are several camps 14th , 15th , 16 , 17A , 17B intended. The bearings designed as roller bearings 14th , 15th , 16 are present in an axial direction X of the gas turbine engine 1 front storage chamber 12th arranged, while the bearings also designed as roller bearings 17A and 17B in one in the axial direction X of the gas turbine engine 1 rear storage chamber 13th are mounted.

In addition, the housing includes 11 of the gas turbine engine 1 an in 2 intermediate housing shown in more detail 18th . Furthermore, the gas turbine engine 1 several, in the axial direction X of the gas turbine plant 1 adjoining and interconnected housing parts. The upstream inlet area 3 is in this case formed by an inlet housing, on which there is a downstream in the assembled state of the gas turbine engine 1 the brass 5 enclosing fan housing connects. The intermediate housing closes downstream of the fan housing 18th on, to which a sheath current housing is connected downstream 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 is via the intermediate housing 18th can be connected to an aircraft, so that during operation of the gas turbine engine 1 occurring loads via the intermediate housing 18th to a not shown, with the intermediate housing 18th in operative connection bringable support beam of the gas turbine engine 1 guided and derived from a structure of the aircraft. Such a gas turbine engine 1 is also known as a case-mounted engine.

The following is the intermediate housing 18th of the gas turbine engine 1 described in more detail that extends from the central axis 19th of the gas turbine engine 1 or the intermediate housing 18th in the radial direction Y extends outward and from that in the radial direction Y at least one area of the core flow channel and one area of the secondary flow channel 2 is limited.

The intermediate housing 18th In the present case, it comprises two each annular housing areas 20th , 21 that are about between the housing areas 20th , 21 radially extending as well as in the circumferential direction U of the gas turbine engine 1 spaced struts 22nd are firmly connected to each other. From surfaces facing each other 23 , 24 of the two housing parts 20th , 21 becomes part of the bypass duct 2 each in the radial direction Y limited. The housing parts 20th , 21 are in the embodiment shown over eight struts 22nd connected to each other, the struts 22nd each end in the area of the surfaces 23 and 24 with the housing areas 20th , 21 are connected.

The struts, in particular evenly distributed around the circumference 22nd , which are also referred to as struts, are both in the area of the fluid flow or air flow A. in the bypass duct 2 facing front 25th as well as in the area of a back 26th aerodynamically shaped and serve in addition to the flow guidance in the flow cross-section 2 especially for the transfer of loads from the core area of the gas turbine engine 1 radially outwards. For the implementation of service lines from a radially inside of the radially inner housing area 21 lying engine area 27 to a radially outside of the radially outer housing part 20th lying engine area 28 and / or for weight loss there is the possibility that one, several or all of the struts 22nd are made hollow.

2 shows the intermediate housing 18th in the installation position of the gas turbine engine 1 on an airplane or aircraft. A horizontal plane of symmetry HE of the gas turbine engine 1 and thus also of the intermediate housing 18th runs through two essentially horizontally aligned struts 22A and 22B as well as through the central axis 19th . This divides the horizontal plane of symmetry HE the intermediate housing 18th into an upper part and a lower part. Inside the radially inner housing area 21 is in the present case the front storage chamber 12th arranged, the one in the radially inner engine area 27 represents arranged device and the operation of the gas turbine engine 1 is charged with oil.

That of the front storage chamber 12th supplied oil is supplied by an in 3 return shown in more detail 31 the storage room 12th in the area of a lower strut 22C from the inner engine area 27 radially outwards in the direction of the radially outer engine area 28 guided. The lower strut runs 22C in the in 2 Installation position shown by the below the horizontal symmetry plane HE lying area of the flow cross-section or the bypass channel 2 . The lower strut 22C is in 2 circumferentially in a so-called 6 o'clock position of the gas turbine engine 1 arranged and thus runs perpendicular to the horizontal plane of symmetry HE radially downwards through the bypass duct 2 .

This is also due to the force of gravity acting on the oil through the strut 22C guided oil is downstream of the lower strut 22C initially in an oil tank 29 collected, the one in the radially outer engine area 28 is arranged. From the oil tank 29 the oil is in the radially outer area of the engine 28 in the circumferential direction U to another strut 22D guided. The further strut 22D is in the in 2 Installation position of the gas turbine engine shown 1 in one above the horizontal plane of symmetry HE lying area of the flow cross-section 2 arranged. The further or upper strut is located here 22D at a so-called 12 o'clock position and is in the circumferential direction U of the gas turbine engine 1 opposite the lower strut 22C swiveled by 180 ° in the bypass duct 2 arranged. That of the upper strut 22D The oil supplied thus also flows out of the radially outer area of the engine due to the force of gravity acting on the oil 28 in the direction of the radially inner engine area 27 .

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

If the one in the area of the upper strut 22D additionally created cooling possibility or cooling capacity for temperature control of the oil of the gas turbine engine 1 Should not be sufficient, it can be provided that that from the return 31 the front storage chamber 12th extracted oil from the radially inner engine area 27 into another strut 22E in the direction of the radially outer engine area 28 is initiated. The further strut 22E is also in the one below the horizontal plane of symmetry HE lying area of the bypass duct 2 arranged. This ensures that it is in the lower side strut 22E introduced oil by gravity radially in the direction of the radially outer engine area 28 flows. In addition, the oil is fed into the lateral lower strut via an appropriate device, such as a feed pump or the like 22E such an impulse is imposed that the oil inside the lower side strut 22E from one of the radially outer engine area 28 facing end of the lateral lower strut 22E back to the radially inner engine area 27 flows back and then into the lower strut 22C is initiated. This becomes the storage room 12th removed oil in the area of the lower side strut 22E also through the side stream A. cooled, the outside of the lower side strut 22E flows towards.

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

Alternatively, it can also be provided that the oil is independent of the guidance of the oil between the lower strut 22C and the top strut 22D in the additional death 22F is initiated.

The extra strut 22F is in the circumferential flow path of the oil between the lower strut 22C and the top strut 22D upstream of the upper strut 22D and above the horizontal plane of symmetry HE in the bypass duct 2 arranged running. The oil is initially taken from the radially outer area of the engine 28 through the inside of the side upper strut 22F radially inwards in the direction of the radially inner engine area 27 guided. Once the oil is inside the extra strut 22F that of the radially inner engine area 27 facing end of the additional strut 22F has reached, the oil flows in the upper side strut 22F back again in the direction of the radially outer engine area 28 and will there to the mouth area of the upper strut 22D guided. The oil is also in the area of the upper side strut 22F through the outside of the side upper strut 22F flowing around secondary stream A. chilled.

The oil is inside the lower side strut 22E and also inside the side upper strut 22F each up to a defined area of the struts 22E and 22F guided. The defined areas point in the radial direction Y of the intermediate housing 18th each a defined distance from the inner engine area 27 or from the outer engine area 28 on. The distances for the in 2 illustrated embodiment of the gas turbine engine 1 each of the same size and essentially corresponds to the entire radial distance between the outside 24 of the radially inner housing area 21 and the inside 23 of the radially outer housing area 20th .

3 shows a greatly simplified block diagram of an oil circuit 30th of the gas turbine engine 1 according to 1 . According to the representation 3 the oil in the area of the return line is correspondingly 31 from the front storage chamber 12th into a return line RL1 initiated. In the present case, the return line runs RL1 in the manner described above only through the lower strut 22C . The return line RL1 is with one suction side of a return pump 32 connected through which the oil from the front storage chamber 12th is sucked off. The return pump 32 pumps the oil into the oil tank 29 . In addition, the return pump 32 as in 3 shown, also with a rewind 33 the rear storage chamber 13th be connected and also from the rear storage chamber 13th Suck off the oil.

A feed pump 34 pumps oil from the oil tank 29 towards a filter 35 , in the area of which the one from the oil tank 29 removed oil is filtered. Parallel to the oil filter 35 is a bypass valve 36 provided over the by the feed pump 34 Oil pumped when the pressure loss in the area of the oil filter is too high 35 on the oil filter 35 can be passed by. In addition, one is for the oil filter 35 parallel oil path 36A a differential pressure transducer 36B provided over 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 is above the specific pressure difference 36 operable.

Downstream of the oil filter 35 as well as the bypass valve 36A the oil is going towards a heat exchanger 37 out, in the area of which the oil is tempered or cooled by means of the aircraft's fuel. The fuel is delivered through a fuel line T1 through the heat exchanger 37 guided. Downstream of the heat exchanger 37 the oil is directed towards the two storage chambers 12th and 13th as well as in the direction of an auxiliary device transmission 38A of the gas turbine engine 1 guided 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 released through ventilation lines V12 and V13 from the two storage chambers 12th and 13th towards an oil separator 38 which is also known as a breather. In the area of the oil separator 38 the oil is separated from the air laden with oil and from the return pump in a manner known per se 32 sucked in and into the oil tank 29 initiated. The air cleaned of oil is released from the oil separator 38 to the environment of the gas turbine engine 1 submitted. Between the heat exchanger 37 and the two storage chambers 12th runs a line L1 . The rear storage room 13th is available via a return line RL2 with the return pump 32 in connection.

In the oil flow path between the oil filter 35 and the heat exchanger 37 another line branches off L2 starting over the that from the oil tank 29 removed and in the oil filter 35 filtered oil in the outer engine area 28 circumferentially to the upper strut 22D guided and through the top strut 22D radially inwards into the inner engine area 27 is initiated. From there that is done through the top strut 22D guided oil into the front storage chamber 12th initiated. Furthermore is in the further line L2 a flow limiter 50 provided with a preferably variable throttle effect, whereby the cooling capacity of the gas turbine engine 1 is limited or adjustable.

The oil is in this way in the interior of the front bearing chamber 12th initiated that the oil on the inside of the bearing chamber wall from an above the horizontal plane of symmetry HE lying area of the storage chamber 12th radially downwards in the direction of the return 31 the front storage chamber 12th flows. This ensures that the through the storage chamber 12th guided oil in the area of the outer wall of the bearing chamber 12th is further tempered or cooled.

It can be provided that the inside of the outer wall of the front storage chamber 12th is carried out with oil guide grooves or the like, in which the in the storage chamber 12th introduced oil to a defined extent through the storage chamber 12th in the direction of the return 31 to be led.

4th to 6th each shows a cross-sectional view of various embodiments of the top strut 22D , which is hollow on the inside, along an in 2 section line IV- shown in more detail IV. It should be noted that each of the struts 22nd of the intermediate housing 18th can be carried out in the manner described below.

The in 4th shown embodiment of the upper strut 22D an oil guide area extends 40 the upper strut 22D over the entire cross-section of the upper strut 22D . So that in the upper strut 22D introduced oil to the desired extent over the entire inner surface of the inside 41A the outer wall 41 the upper strut 22D distributed from the radially outer engine area 27 in the direction of the radially inner engine area 28 flows in a distributed manner, includes the oil guide area 40 the upper strut 22D from the outer wall 41 in the oil guide area 40 protruding wall areas 42 .

The in 5 illustrated embodiment of the upper strut 22D includes the oil routing area 40 the upper strut 22D each a circumferential gap 43 that goes from one to the outer wall 41 or the inside 41A the outer wall 41 the upper strut 22D spaced inner wall 44 is limited.

The circumferential gap 43 of the oil guide area 40 the upper strut 22D is with the in 6th Embodiment shown in areas in each case by bulkheads 45 in the circumferential direction of the upper strut 22D into channel-like gap sections 46 divided. The bulkheads 45 each extend between the outer wall 41 and the inner wall 44 the upper strut 22D .

It is also possible to provide 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. Since the direction of flow in closed structures is defined by the applied delivery pressure of the oil, any flow direction inside the strut or struts can be implemented.

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

It goes without saying that further efforts are also at the discretion of the person skilled in the art 22C , 22E , 22F in each to 4th to 6th Execute the scope described in more detail in order to achieve the greatest possible cooling capacity in the area of the intermediate housing 18th to be able to provide.

Furthermore, there is also the possibility, in addition to or as an alternative to those in the bypass duct 2 arranged struts 22nd also to carry out a housing of an aircraft engine according to the present disclosure, the struts of which through the flow cross-section of the core flow B. run in order to cool or temper the oil in their area by the core flow flowing onto the struts.

List of reference symbols

1

Gas turbine engine

2

Sidestream channel

3

Inlet area

4th

Wind players

5

Engine core

6th

Compressor device

7th

burner

8th

Turbine device

9

first wave, low pressure wave

10

second shaft, high pressure turbine

11

casing

12th

front storage chamber

13th

rear storage chamber

14th

warehouse

15th

warehouse

16

warehouse

17A, 17B

warehouse

18th

Intermediate housing

19th

Central axis, central axis

20th

radially outer housing area

21

radially inner housing area

22nd

strut

22A, 22B

strut

22C

lower strut

22D

upper strut

22E

further strut

22F

additional strut

23

Inside of the housing area 20

24

Outside of the housing area 21

25th

Front of the strut

26th

Back of the strut

27

radially inner engine area

28

radially outer engine area

29

Oil tank

30th

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 filter

36

Bypass valve

36A

Oil path

36B

Differential pressure transducer

37

Heat exchanger

38

Oil separator, breather

38A

Auxiliary equipment gearbox

39

Differential pressure transducer

40

Oil guide area

41

outer wall of the upper strut 22D

41A

Inside 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.

Sidestream

B.

Core stream

HE

Horizontal symmetry plane

L1, L2

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

QUOTES INCLUDED IN THE DESCRIPTION

This list of the documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• WO 2019/086065 A1 [0002]
• FR 3030627 B1 [0003]
• US 2018/0306042 A1 [0004]
• US 2011/0268562 A1 [0005]

Claims (15)

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 in the inner engine area ( 27) and / or in the outer engine area (28) arranged device (12) to which oil can be applied, the inner engine area (27) and the outer engine area (28) being in operative connection with one another via struts (22, 22A to 22F) which extend radially through the flow cross section (2) and are spaced apart in the circumferential direction (U) of the flow cross section (2), and wherein oil from a return (31) of the device (12), in the area of which the operating temperature is greater 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) can be guided from the inner engine area (27) into the outer engine area (28) and / or from the outer engine area (28) into the inner engine area (27). Gas turbine engine after Claim 1 , characterized in that at least in the area of one of the struts (22C, 22D), which in the installed position of the gas turbine engine (1) through an area of the flow cross-section (2) lying below or above a horizontal plane of symmetry (HE) of the gas turbine engine (1) ) runs through the flow cross-section (2) from the inner or outer engine area (27 or 28) into the outer or inner engine area (28 or 27) and in the outer or inner engine area (27 or 28) in the circumferential direction (U) at least one further strut (22D) can be guided, 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 flows through the flow cross section (2) the outer or inner engine area (28 or 27) can be introduced into the inner or outer engine area (27 or 28). Gas turbine engine after 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). Gas turbine engine after 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 is a defined in the radial direction (Y) Distance from the outer or inner engine area (28), can be guided and can be introduced back into the outer or inner engine area (28) in the additional strut (22E) from the defined area of the additional strut (22E). Gas turbine engine after 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) in the additional strut (22F) can be introduced. Gas turbine engine after Claim 5 , characterized in that an oil collecting area is provided in the inner 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). Gas turbine engine after Claim 5 or 6th , characterized in that at least one return pump (32) is provided in the flow path of the oil between the device (12) and the strut (22C) and / or the additional strut (22F). Gas turbine engine according to one of the Claims 5 to 7th , 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 further 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. Gas turbine engine according to one of the Claims 1 to 8th , characterized in that at least one of the struts (22D) has at least one oil guide region (40) running inside the strut (22D), which in each case extends inside the strut (22D) over the entire inner cross section of the strut (22D). Gas turbine engine after Claim 9 , characterized in that the oil guide area (40) is delimited by the outer wall (41) of the at least one strut (22D). Gas turbine engine after Claim 9 or 10 , characterized in that the oil guide area (40) of the at least one strut (22D) has wall areas (42) protruding from the outer wall (41) of the strut (22D) into the oil guide area (40). Gas turbine engine according to one of the Claims 9 to 11 , characterized in that the oil guide area (40) of the at least one strut (22D) each comprises a circumferential gap (43) which is delimited by the inner wall (44) spaced apart from the outer wall (41) of the strut (22D). Gas turbine engine after Claim 12 , characterized in that the circumferential gap (43) of the oil guide area (40) of the at least one strut (22D) is at least partially subdivided by bulkheads (45) in the circumferential direction of the at least one strut (22D) into channel-like gap sections (46), wherein the bulkheads (45) each extend between the outer wall (40) and the inner wall (44) of the at least one strut (22D). Gas turbine engine according to one of the Claims 1 to 13th , characterized in that the oil can be introduced into at least one of the struts (22) via at least one nozzle. Gas turbine engine according to one of the Claims 1 to 14th , characterized in that the device (12) is designed as a bearing chamber and the oil guided through the further strut (22D) into the inner engine area (27) into an inner area of the bearing chamber (12) which is above the horizontal symmetry Plane (HE) of the storage chamber (12) is arranged, is introduced in such a way that the oil along an inner side of the storage chamber (12) in the direction of an extraction point for the oil from the storage chamber (12) located below the horizontal plane of symmetry (HE) ) flows.

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