GAS TURBINE ENGINE

Abstract

A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is the predefined flow rate or is a corresponding operational value or is greater than or equal to a further corresponding operational value.

Claims

1. A gas turbine engine for an aircraft comprising: an engine core comprising at least one turbine, at least one compressor and at least one shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; a first oil circuit, a second oil circuit and at least a third oil circuit; the first oil circuit, the second oil circuit and the third oil circuit fluidly coupled with at least one inlet of the gearbox as well as with at least one outlet of the gearbox; the first oil circuit and the second oil circuit each including at least one pump driven by the shaft; the third oil circuit including a pump; and the outlet of the gearbox including a device configured to direct oil from the gearbox to the first oil circuit and/or to the second oil circuit and/or to the third oil circuit when the feeding to the gearbox is exceeding a predefined oil flow rate, or is deviating at least one operational value corresponding with that oil flow rate, and is configured to direct the oil from the gearbox to the third oil circuit when the feeding to the gearbox is less than or equal to the predefined flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

2. The gas turbine engine according to claim 1, wherein: the turbine is a first turbine, the compressor is a first compressor, and the shaft is a first core shaft; the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.

3. The gas turbine engine according to claim 1, wherein: the first oil circuit is including a heat exchanger.

4. The gas turbine engine according to claim 1, wherein: the second oil circuit is including a heat exchanger.

5. The gas turbine engine according to claim 1, wherein: the first oil circuit and the second oil circuit each are including a scavenge pump and a feeding pump driven by the core shaft.

6. The gas turbine engine according to claim 1, wherein: the third oil circuit is including a pump driven by the first core shaft, the second core shaft or by the fan or by a separate drive unit.

7. The gas turbine engine according to claim 1, wherein: the device is including an oil reservoir from which oil received from the gearbox can be directly conducted back into the gearbox back via the third oil circuit, and in the gearbox via the first oil circuit and the second oil circuit, whereby oil is conducted from the oil reservoir only via the third oil circuit directly to the inlet of the gearbox as long as a filling level of the oil reservoir is less than a defined filling level of the oil reservoir, and oil can be directed via the first oil circuit and via the second oil circuit to the oil tank as soon as the defined filling level of the oil reservoir is reached.

8. The gas turbine engine according to claim 1, wherein: the device is including a first valve unit and a second valve unit whereby the first valve unit is configured to block the connection between the outlet of the gearbox and the inlet of the oil tank via the first oil circuit, and is configured to unblock the connection between the outlet of the gearbox and the inlet of the gearbox via the third oil circuit as long as the feeding to the gearbox from the first oil circuit is less than or equal to the predefined oil flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

9. The gas turbine engine according to claim 8, wherein: the second valve unit is configured to block the connection between the outlet of the gearbox and the inlet of the gearbox via the second oil circuit as long as the feeding to the gearbox from the second oil circuit is less than or equal to the predefined oil flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

10. The gas turbine engine according to claim 8, wherein: the first valve unit is comprising a solenoid valve and a 5/2 directional control valve whereby the solenoid valve is configured to apply a feeding pressure in the first oil circuit upstream of the inlet of the gearbox to a control surface of a valve control spool of the 5/2 directional control valve in a first operational state of the solenoid valve.

11. The gas turbine engine according to claim 10, wherein: a control line between the solenoid valve and the 5/2 directional control valve is fluidly coupled upstream of the 5/2 directional control valve with the scavenge pump by a throttle.

12. The gas turbine engine according to claim 8, wherein: the second valve unit is comprising a solenoid valve and a 2/2 directional control valve whereby the solenoid valve is configured to apply a feeding pressure in the second oil circuit upstream of the inlet of the gearbox to a control surface of a valve control spool of the 2/2 directional control valve in a first operational state of the solenoid valve.

13. The gas turbine engine according to claim 12, wherein: a control line between the solenoid valve and the 2/2 directional control valve is fluidly coupled upstream of the 2/2 directional control valve with the scavenge pump by a throttle.

14. The gas turbine engine according to claim 1, wherein: the first oil circuit and the second oil circuit are fluidly coupled with an inlet of an oil tank as well as with an outlet of the oil tank, and the first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the gearbox.

15. The gas turbine engine according to claim 1, wherein: a throttle is positioned between the inlet of the gearbox and the feeding pump of the second oil circuit.

Description

[0080] Embodiments will now be described by way of example only, with reference to the Figures, in which:

[0081] FIG. 1 is a sectional side view of a gas turbine engine;

[0082] FIG. 2 is a close up sectional side view of an upstream portion of a gas turbine engine;

[0083] FIG. 3 is a partially cut-away view of a gearbox for a gas turbine engine;

[0084] FIG. 4 a first embodiment of an oil system of a gas turbine engine;

[0085] FIG. 5 a second embodiment of an oil system of a gas turbine engine; and

[0086] FIG. 6 a third embodiment of an oil system of a gas turbine engine.

[0087] FIG. 1 illustrates a gas turbine engine 10 having a principal rotational axis 9. The engine 10 comprises an air intake 12 and a propulsive fan 23 that generates two airflows: a core airflow A and a bypass airflow B. The gas turbine engine 10 comprises a core 11 that receives the core airflow A. The engine core 11 comprises, in axial flow series, a low pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, a low pressure turbine 19 and a core exhaust nozzle 20. A nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18. The bypass airflow B flows through the bypass duct 22. The fan 23 is attached to and driven by the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30.

[0088] In use, the core airflow A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 where further compression takes place. The compressed air exhausted from the high pressure compressor 15 is directed into the combustion equipment 16 where it is mixed with fuel and the mixture is combusted. The resultant hot combustion products then expand through, and thereby drive, the high pressure and low pressure turbines 17, 19 before being exhausted through the nozzle 20 to provide some propulsive thrust. The high pressure turbine 17 drives the high pressure compressor 15 by a suitable interconnecting shaft 27. The fan 23 generally provides the majority of the propulsive thrust. The epicyclic gearbox 30 is a reduction gearbox.

[0089] An exemplary arrangement for a geared fan gas turbine engine 10 is shown in FIG. 2. The low pressure turbine 19 (see FIG. 1) drives the shaft 26, which is coupled to a sun wheel, or sun gear 28 of the epicyclic gear arrangement 30. Radially outwardly of the sun gear 28 and intermeshing therewith is a plurality of planet gears 32 that are coupled together by a planet carrier 34. The planet carrier 34 constrains the planet gears 32 to precess around the sun gear 28 in synchronicity whilst enabling each planet gear 32 to rotate about its own axis. The planet carrier 34 is coupled via linkages 36 to the fan 23 in order to drive its rotation about the engine axis 9. Radially outwardly of the planet gears 32 and intermeshing therewith is an annulus or ring gear 38 that is coupled, via linkages 40, to a stationary supporting structure 24.

[0090] Note that the terms low pressure turbine and low pressure compressor as used herein may be taken to mean the lowest pressure turbine stages and lowest pressure compressor stages (i.e. not including the fan 23) respectively and/or the turbine and compressor stages that are connected together by the interconnecting shaft 26 with the lowest rotational speed in the engine (i.e. not including the gearbox output shaft that drives the fan 23). In some literature, the low pressure turbine and low pressure compressor referred to herein may alternatively be known as the intermediate pressure turbine and intermediate pressure compressor. Where such alternative nomenclature is used, the fan 23 may be referred to as a first, or lowest pressure, compression stage.

[0091] The epicyclic gearbox 30 is shown by way of example in greater detail in FIG. 3. Each of the sun gear 28, planet gears 32 and ring gear 38 comprise teeth about their periphery to intermesh with the other gears. However, for clarity only exemplary portions of the teeth are illustrated in FIG. 3. There are four planet gears 32 illustrated, although it will be apparent to the skilled reader that more or fewer planet gears 32 may be provided within the scope of the claimed invention. Practical applications of a planetary epicyclic gearbox 30 generally comprise at least three planet gears 32.

[0092] The epicyclic gearbox 30 illustrated by way of example in FIG. 2 and FIG. 3 is of the planetary type, in that the planet carrier 34 is coupled to an output shaft via linkages 36, with the ring gear 38 fixed. However, any other suitable type of epicyclic gearbox 30 may be used. By way of further example, the epicyclic gearbox 30 may be a star arrangement, in which the planet carrier 34 is held fixed, with the ring (or annulus) gear 38 allowed to rotate. In such an arrangement the fan 23 is driven by the ring gear 38. By way of further alternative example, the gearbox 30 may be a differential gearbox in which the ring gear 38 and the planet carrier 34 are both allowed to rotate.

[0093] It will be appreciated that the arrangement shown in FIG. 2 and FIG. 3 is by way of example only, and various alternatives are within the scope of the present disclosure. Purely by way of example, any suitable arrangement may be used for locating the gearbox 30 in the engine 10 and/or for connecting the gearbox 30 to the engine 10. By way of further example, the connections (such as the linkages 36, 40 in the FIG. 2 example) between the gearbox 30 and other parts of the engine 10 (such as the input shaft 26, the output shaft and the fixed structure 24) may have any desired degree of stiffness or flexibility. By way of further example, any suitable arrangement of the bearings between rotating and stationary parts of the engine (for example between the input and output shafts from the gearbox and the fixed structures, such as the gearbox casing) may be used, and the disclosure is not limited to the exemplary arrangement of FIG. 2. For example, where the gearbox 30 has a star arrangement (described above), the skilled person would readily understand that the arrangement of output and support linkages and bearing locations would typically be different to that shown by way of example in FIG. 2.

[0094] Accordingly, the present disclosure extends to a gas turbine engine having any arrangement of gearbox styles (for example star or planetary), support structures, input and output shaft arrangement, and bearing locations.

[0095] Optionally, the gearbox may drive additional and/or alternative components (e.g. the intermediate pressure compressor and/or a booster compressor).

[0096] Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. For example, such engines may have an alternative number of compressors and/or turbines and/or an alternative number of interconnecting shafts. By way of further example, the gas turbine engine shown in FIG. 1 has a split flow nozzle 20, 22 meaning that the flow through the bypass duct 22 has its own nozzle that is separate to and radially outside the core engine nozzle 20. However, this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass duct 22 and the flow through the core 11 are mixed, or combined, before (or upstream of) a single nozzle, which may be referred to as a mixed flow nozzle. One or both nozzles (whether mixed or split flow) may have a fixed or variable area. Whilst the described example relates to a turbofan engine, the disclosure may apply, for example, to any type of gas turbine engine, such as an open rotor (in which the fan stage is not surrounded by a nacelle) or turboprop engine, for example.

[0097] The geometry of the gas turbine engine 10, and components thereof, is defined by a conventional axis system, comprising an axial direction (which is aligned with the rotational axis 9), a radial direction (in the bottom-to-top direction in FIG. 1), and a circumferential direction (perpendicular to the page in the FIG. 1 view). The axial, radial and circumferential directions are mutually perpendicular.

[0098] FIG. 4 shows a first embodiment of an oil system 42 of the gas turbine engine 10. The oil system 42 comprises a first oil circuit 43, a second oil circuit 45 and at least a third oil circuit 47. The first oil circuit 43, the second oil circuit 45 and the third oil circuit 45 are fluidly coupled with a common outlet 50 of the gearbox 30. Further, the first oil circuit 43, the second oil circuit 45 and the third oil circuit 45 each are fluidly coupled with a separate inlet 48, 49, 56 of the gearbox 30.

[0099] The first oil circuit 43 and the second oil circuit 45 each include a pump 57, 58 driven by the core shaft 26 or the core shaft 27. In addition, the third oil circuit 47 includes a pump 61 driven by the fan 23 or the core shaft 27 or any other suitable drive unit, for example an electric drive unit or the like.

[0100] The outlet 50 of the gearbox includes a device 63 configured to direct oil from the gearbox 30 to the first oil circuit 43, to the second oil circuit 45 and depending on the respective embodiment of the gas turbine engine 10 to the third oil circuit 47 when the feeding to the gearbox 30 is exceeding a predefined oil flow rate, or is deviating an operational value corresponding with that oil flow rate. Additionally, the device 63 is configured to direct the oil from the gearbox 30 solely to the third oil circuit 47 when the feeding to the gearbox is less than or equal to the predefined flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

[0101] In case that oil is directed to the third oil circuit 47 by the device 63 over the entire operating range of the gas turbine engine 10 the third oil circuit 47 comprises in a further embodiment a valve unit 85 between the outlet 50 and the inlet 56 of the gearbox 30. The valve unit 85 is configured to direct oil from the outlet 50 to the second oil circuit 45 through an optional duct 86 when the feeding to the gearbox 30 is exceeding the predefined oil flow rate or is deviating the at least one operational value.

[0102] FIG. 5 shows a second embodiment of an oil system 42 of the gas turbine engine 10. The oil system 42 comprises a first oil circuit 43 including a heat exchanger 44, a second oil circuit 45 including a heat exchanger 46 and at least a third oil circuit 47. The first oil circuit 43 and the second oil circuit 45 are fluidly coupled with an inlet 48, 49 of the gearbox 30 as well as with an outlet 50 of the gearbox 30. Furthermore, the second oil circuit 45 is configured to direct oil from an oil tank 53 to a turbomachinery 68 of the gas turbine engine 10. The inlet 48 is fluidly coupled with an oil transfer unit 66 which is arranged inside the gearbox 30. In contrast, the inlet 49 is fluidly coupled to a further oil transfer unit 62 of the gearbox 30 which is located inside the gearbox 30. Moreover, the first oil circuit 43 and the second oil circuit 45 are fluidly coupled with an inlet 51, 52 of the oil tank 53 as well as with an outlet 54, 55 of the oil tank 53. The third oil circuit 47 is fluidly coupled with an inlet 56 of the gearbox 30 as well as with the outlet 50 of the gearbox 30.

[0103] Further, the first oil circuit 43 and the second oil circuit 45 each include a scavenge pump 57, 58 and a feeding pump 59, 60 driven by the core shaft 26 and accordingly by an auxiliary gearbox 31 of the gas turbine engine 10. In addition, the third oil circuit 47 includes a feeding pump 61 driven by the fan 23.

[0104] Moreover, the third oil circuit 47 may comprise an additional oil tank and a scavenge pump between the oil reservoir 64 and the feeding pump 61.

[0105] The first oil circuit 43 and the second oil circuit 45 are configured to receive oil from the oil tank 53 and to direct the received oil to the gearbox 30. The third oil circuit 47 is configured to receive oil from the outlet 50 of the gearbox 30 and to direct the received oil to the inlet 49 and the oil transfer unit 62 of the gearbox 30.

[0106] The heat exchanger 44 of the first oil circuit 43 is arranged between the feeding pump 59 and the inlet 48 of the gearbox 30. The heat exchanger 46 of the second oil circuit 45 is arranged between the feeding pump 60 and an optional throttle 67 which is positioned between the inlet 49 of the gearbox 30 and the feeding pump 60 of the second oil circuit 45.

[0107] The outlet 50 of the gearbox includes a device 63 configured to direct oil from the gearbox 30 to the first oil circuit 43, to the second oil circuit 45 and to the third oil circuit 47 when the feeding to the gearbox 30 is exceeding a predefined oil flow rate, or is deviating an operational value corresponding with that oil flow rate. Additionally, the device 63 is configured to direct the oil from the gearbox 30 to the third oil circuit 47 when the feeding to the gearbox is less than or equal to the predefined flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

[0108] For this purpose the device 63 includes an oil reservoir 64 from which oil received from the gearbox 30 can be directly conducted back into the gearbox 30 via the third oil circuit 47, and into the oil tank 53 via the first oil circuit 43 and the second oil circuit 45. Oil is conducted from the oil reservoir 64 only via the third oil circuit 47 directly to the inlet 56 of the gearbox 30 as long as a filling level of the oil reservoir 64 is less than the defined filling level 65 of the oil reservoir 64. In addition, oil is directed via the first oil circuit 43 and via the second oil circuit 45 to the oil tank 53 and via the third oil circuit 47 to the inlet 56 as soon as the defined filling level 65 of the oil reservoir 64 is reached.

[0109] To protect the journal bearings of the gearbox 30 against the single point failure threat of loss of oil from the oil system 42, the oil tank 53 incorporates offset outlets 25, 29 to each of the oil circuits 43, 45. The turbomachinery circuit 45 offset outlet 29 is positioned higher in the oil tank 53 than the offset outlet 25 of the first circuit 43 feeding solely to the gearbox 30. In the event of low oil levels in the oil tank 53 the turbomachinery circuit 45 will generate a low oil pressure warning or another warning signal first without the first circuit 43 having yet been affected. The level of offset can be designed such that, under all reasonable rates of oil loss, the pilot has reacted to the warning before the first oil circuit 43 feed to the journal bearings is lost or reduced.

[0110] A third embodiment of the oil system 42 of the gas turbine engine 30 is shown in FIG. 6. The structure and the function of the oil system 42 according to FIG. 6 corresponds substantially to the structure and the function of the oil system 42 according to FIG. 5. However, the device 63 of the oil system 42 according to FIG. 6 differs from the device 63 of the oil system 42 pursuant to FIG. 5.

[0111] The device 63 includes a first valve unit 69 and a second valve unit 70. The first valve 69 unit is configured to block the connection between an outlet 90 of the gearbox and the inlet 51 of the oil tank 53 via the first oil circuit 43, and is configured to unblock the connection between an outlet 91 and the inlet 56 of the gearbox 30 via the third oil circuit 47 as long as the feeding to the gearbox 30 from the first oil circuit 43 is less than the predefined oil flow rate or the corresponding operational pressure value.

[0112] The first valve unit 69 comprises a solenoid valve 71 and a 5/2 directional control valve 72. The solenoid valve 71 is configured to apply a feeding pressure in the first oil circuit 43 upstream of the inlet 48 of the gearbox 30 to a control surface 73 of a valve control spool 74 of the 5/2 directional control valve 72 in a first operational state of the solenoid valve 71. The solenoid valve 71 can be switched against a spring load from a second operational state into the first operational state by an appropriate electrical control signal. In the second operational state of the solenoid valve 71 the feeding pressure in the first oil circuit 43 is not applied to the spool 74 of the 5/2 directional control valve 72. A control line 75 between the solenoid valve 71 and the 5/2 directional control valve 72 is fluidly coupled upstream of the 5/2 directional control valve 72 with the scavenge pump 57 by a throttle 76.

[0113] A spring load of a spring 92 is applied to the spool 74 of the 5/2 directional control valve 72 in the direction of a first position of the spool 74 in which the outlet 91 of the gearbox 30 is fluidly coupled with the inlet 56 of the gearbox 30 via the third oil circuit 47 and the connection between the outlet 90 and the inlet 51 of the tank 53 via the first oil circuit 43 is blocked by the 5/2 directional control valve 72. The feeding pressure in the first oil circuit 43 could be applied opposed to the spring load to the spool 74 and in the direction of a second position of the spool 74 in such a manner that the spool 74 is moved to the second position by the feeding pressure if the compressive force resulting by the feeding pressure exceeds the spring load. In the second position of the spool 74 the outlet 90 of the gearbox 30 is fluidly coupled with the inlet 51 of the tank 53 via the first oil circuit 43. The outlet 91 of the gearbox 30 is fluidly coupled via the third oil circuit 47 and the 5/2 directional control valve 72 with the inlet 51 of the tank 53 in the second position of the spool 74.

[0114] The second valve unit 70 is configured to block the connection between an outlet 94 of the gearbox 30 and the oil tank 53 via the second oil circuit 45 as long as the feeding to the gearbox 30 from the second oil circuit 45 is less than the predefined oil flow rate or is less than or equal to at least one corresponding operational value or is greater than or equal to at least one further corresponding operational value.

[0115] For this purpose the second valve unit 70 comprises a solenoid valve 77 and a 2/2 directional control valve 78. The solenoid valve 77 is configured to apply a feeding pressure in the second oil circuit 45 upstream of the inlet 49 of the gearbox 30 to a control surface 79 of a valve control spool 80 of the 2/2 directional control valve 78 in a first operational state of the solenoid valve 77. The solenoid valve 77 can be switched against a spring load from a second operational state into the first operational state by an appropriate electrical control signal. In the second operational state of the solenoid valve 77 the feeding pressure in the second oil circuit 45 is not applied to the spool 80 of the 2/2 directional control valve 78. A control line 81 between the solenoid valve 77 and the 2/2 directional control valve 78 is fluidly coupled upstream of the 2/2 directional control valve 78 with the scavenge pump 58 by an optional throttle 82.

[0116] A spring load of a spring 93 is applied to the spool 80 of the 2/2 directional control valve 78 in the direction of a first position of the spool 80 in which the connection between the outlet 94 and the inlet 52 of the tank 53 via the second oil circuit 45 is blocked by the 2/2 directional control valve 78. The feeding pressure in the second oil circuit 45 could be applied opposed to the spring load to the spool 80 and in the direction of a second position of the spool 80 in such a manner that the spool 80 is moved to the second position by the feeding pressure if the compressive force resulting by the feeding pressure exceeds the spring load. In the second position of the spool 80 the outlet 94 of the gearbox 30 is fluidly coupled with the inlet 52 of the gearbox 30 via the second oil circuit 45.

[0117] It is also possible that the first oil circuit 43 and the second oil circuit 45 are including separate oil tanks instead of the common oil tank 53. There are also possible solutions where the two pumps 57, 59 and 58, 60 of each oil circuit 43, 45 are connected with a shear neck drive to couple and de-couple the two units.

[0118] It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.

PARTS LIST

[0119] 9 principal rotational axis [0120] 10 engine [0121] 11 core [0122] 12 air intake [0123] 14 low pressure compressor [0124] 15 high pressure compressor [0125] 16 combustion equipment [0126] 17 high-pressure turbine [0127] 18 bypass exhaust nozzle [0128] 19 low pressure turbine [0129] 20 core exhaust nozzle [0130] 21 nacelle [0131] 22 bypass duct [0132] 23 propulsive fan [0133] 24 stationary supporting structure [0134] 25 offset outlet [0135] 26 shaft [0136] 27 interconnecting shaft [0137] 28 sun gear [0138] 29 offset outlet [0139] 30 epicyclic gearbox [0140] 31 auxilliary gearbox [0141] 32 planet gears [0142] 34 planet carrier [0143] 36 linkage [0144] 38 ring gear [0145] 40 linkage [0146] 42 oil system [0147] 43 first oil circuit [0148] 44 heat exchanger [0149] 45 second oil circuit [0150] 46 heat exchanger [0151] 47 third oil circuit [0152] 48 inlet [0153] 49 inlet [0154] 50 outlet of the gearbox [0155] 51 inlet of the oil tank coupled with the first oil circuit [0156] 52 inlet of the oil tank coupled with the second oil circuit [0157] 53 oil tank [0158] 54 outlet of the oil tank coupled with the first oil circuit [0159] 55 outlet of the oil tank coupled with the second oil circuit [0160] 56 inlet of the gearbox, coupled to the third oil circuit [0161] 57, 58 scavenge pump [0162] 59, 60 feeding pump [0163] 61 feeding pump [0164] 62 oil transfer unit [0165] 63 device [0166] 64 oil reservoir [0167] 65 defined filling level [0168] 66 oil transfer unit [0169] 67 throttle [0170] 68 turbomachinery [0171] 69 first valve unit [0172] 70 second valve unit [0173] 71 solenoid valve [0174] 72 5/2 directional control valve [0175] 73 control surface [0176] 74 valve control spool [0177] 75 control line [0178] 76 throttle [0179] 77 solenoid valve [0180] 78 2/2 directional control valve [0181] 79 control surface [0182] 80 control spool valve [0183] 81 control line [0184] 82 throttle [0185] 85 valve unit [0186] 86 duct [0187] 90 outlet of the gearbox coupled with the first oil circuit [0188] 91 outlet of the gearbox coupled with the third oil circuit [0189] 92 spring of the 5/2 directional control valve [0190] 93 spring of the 2/2 directional control valve [0191] 94 outlet of the gearbox coupled with the second oil circuit [0192] A core airflow [0193] B bypass airflow