Intermediate case of jet turbine engine, and jet turbine engine

FIELD: engines and pumps.

SUBSTANCE: intermediate case of a two-flow jet turbine engine includes at least one annular partition wall for separation of a gas flow into two annular concentric flows, primary and secondary ones respectively. Between inner hub and outer cylindrical shell there located is a variety of radial racks. At least one of the racks is hollow and includes the first part passing through primary flow and the second part passing through secondary flow. In the above radial rack there installed with possibility of being rotated is a transmission shaft of the drive of auxiliary units. The first end of the transmission shaft passes through the inner hub, and the second end passes through outer cylindrical shell. Inner volume of the radial rack consists of one section, in which the transmission shaft is arranged and which forms a channel for lubricating fluid. The other object of the invention is a jet turbine engine containing a chamber with support bearings, a gear box of auxiliary units and the above described intermediate case. Radial rack of the case provides interaction between the chamber and the gear box of auxiliary units.

EFFECT: invention allows laying the auxiliary equipment of the engine in the structural rack of the case.

8 cl, 5 dwg

 

The present invention relates to the field of turbine engines, in particular multistage turbine engines and, in particular, turbojet engines.

From US 3907386 known that the turbofan engine used in civil aviation to ensure the safety of commercial aircraft, intended for the carriage of passengers or freight, generally includes a forward fan rotor, the output of which is divided into two concentric flow - primary and secondary. The primary flow is directed into a turbine, which causes the rotation, in particular, the fan rotor; a secondary thread either emitted directly into the atmosphere, creating the main part of the thrust, or mixed at the outlet of the turbine with the hot primary stream before discharge.

The turbine includes an additional stage of the compressor, a combustion section and multiple turbine stages, the last stage rotates the fan.

Equipment, ensuring the engine is controlled, powered or connected with the surrounding space of the engine through a set of cables, transmission shafts and pipelines, which are referred to by the generic term "accessory". Thus, part of the satellite equipment includes:

the pipelines through which the pass hydraulic fluid, for example, the inlets and outlets of oil for lubrication and cooling;

mechanical organs transmit power for actuation, in particular boxes auxiliary units;

- ventilation ducts;

- electrical cables, United, for example, with different sensors.

As a rule, accessories partially housed in a constructive posts intermediate casing, which radially pass through the primary and secondary flows. Intermediate Carter is an element of a stator in the form of a wheel with a part forming the hub, and a cylindrical outer shell communicating with a gearbox accessory, better known by the English acronym AGB. These two elements are connected by numerous constructive radial racks.

Because the design of the rack is crossed by the gas flow of the engine, it is desirable to reduce their number and their size. For powerful engines of large diameter gasket auxiliary equipment in the racks is not that difficult, as it is enough. The size and number of racks allow you to leave the aisles with a cross section corresponding to the dimensional characteristics of auxiliary equipment. You can, for example, to hold the oil pipeline in the same rack and the drive shaft of the auxiliary units in the adjacent rack. With onee to solve the problem, when the engine has a smaller diameter. In this case, the air-gas path of the engine has a smaller cross-section, and in order not to degrade the aerodynamic characteristics, it is necessary to reduce the number of racks and reduce their sizes. However, as for a powerful engine of large diameter, and engine average diameter accessories remains the same and has essentially the same dimensions. As a result, in the case of the engine of smaller size leaves less space for installation of auxiliary equipment.

For example, as shown in figure 1, the rack 300 of the prior art has a view of a part made by casting metal in an appropriate mold. It is equipped with an oil tube 310 passing through holes 305, 315, made in the upper and lower transverse walls of the rack. These different elements require a sealing means in the border zones at the level of the holes. This tube 310 may be difficult if the installation site in the plane does not provide normal access. This figure shows that, despite the relatively small cross-section relative to the free passage of the rack, the tube occupies a relatively large part, given the need for a free space between the walls. As a result, its overall dimensions leave very mA what about the space for other accessories. In particular, the rotating shaft of the accessory drive is too close to the tube.

From patent application FR 2899272 known intermediate crankcase hour which is a part made by casting together with tight longitudinal bulkhead forming a first passage for oil pipelines and a second pass for the installation of auxiliary equipment and, in particular, mechanical transmission shaft. The integrity of the septum allows you to combine a passage for fluid passage for other accessories and to avoid contamination that could lead to disturbances in normal operation.

Given that the partition is made by casting, the configuration of the openings in the racks is final and does not allow to make any changes or rearrangement of equipment. In addition, the dimensions of this stand are still large and affect the aerodynamic characteristics of the engine.

Therefore, the present invention is a strip of auxiliary equipment via the intermediate casing and, in particular, in a constructive stand referred to the crankcase in such a way as to keep the minimum size and at the same time to optimize the interior space of the rack.

To eliminate the above drawbacks, the applicant proposes sub is full-time Carter turbojet engine, containing, between the inner hub and outer cylindrical rings, set of radial struts, at least one of which is hollow and forms a passage for one or more types of accessories turbojet engine, while in the above-mentioned radial rack rotatably installed radial transmission shaft accessory drive, with the first end of the transmission shaft passes through the inner hub and the second end passes through the outer cylindrical shell, wherein the internal volume of the radial rack consists of a single compartment, which houses the transmission shaft and which forms a channel for lubricant.

Carter, in accordance with the present invention, allows you to combine within a single compartment of limited size channel for lubricating oil and a passage for the shaft, which are usually separated. Such housing with racks of reduced size allows you to cut the middle section of the racks in the primary and secondary flows.

Between the ends of the transmission shaft and the holes formed in the inner hub and an outer cylindrical shell, respectively, leave calibrated gaps. Measured gaps allow you to adjust the flow of lubricating fluid between p the Central chamber turbojet engine, partially bounded by inner hub, and the inner radial displacement of the rack and boxes of engine accessory drives, partially constrained outer cylindrical shell.

According to another distinctive feature of the invention, the crankcase contains at least one annular partition separating the gas stream into two annular concentric flow (R and S), with a radial strut contains the first part C1 passing through the primary flow P, the second part C2 passing through the secondary stream S, with S1 rack is narrower than the portion C2.

The thickness of hours determined so that the hour had minimal volume in the path of the primary beam, which has a small section.

The radial part of the rack passing through the secondary thread (S), contains a longitudinal reinforcing rib, preferably made with.

Reinforcing ribs help to improve the rigidity of the rack and to prevent it from warping, i.e. compression stand on its ends. Preferably the rib perform delicate so as not to increase the mass of the radial hours.

Preferably the transmission shaft is made of monoblock type.

The object of the invention is also a turbojet engine, containing a camera with bearings, a box of auxiliary drives Agra is the ATA and intermediate Carter, mentioned radial strut which provides communication between the said chamber and the said gearbox auxiliary units.

Preferably box accessory drivers contains the oil reservoir which communicates with the chamber via a radial rack.

What follows is a description of a variant implementation of the invention with reference to the accompanying drawings, on which:

figure 1 is a view in longitudinal section of the rack intermediate casing of the prior art;

figure 2 is a view in longitudinal section of a turbojet engine with a crankcase in accordance with the present invention;

figure 3 is a view in longitudinal section of the rack intermediate casing shown in figure 2;

4 is a view of the rack shown in figure 3, in axial section along the section plane A-A;

5 is a view of the rack shown in figure 3, in axial section along the section plane B-C.

Figure 2 shows the intermediate crankcase 100 with a Central hub 1 and the outer shell 2, the United radial counter 16, located vertically at the bottom. The Central hub 1 partially restricts the volume of the anterior chamber 10 turbojet engine, which is equipped with bearings 6, supporting the rotor shafts of the low pressure (LP) and high pressure (HP). On the outer cylindrical cowling 2 crankcase is 100 installed box 20 of engine accessory drives. Auxiliary units are driven monoblock transmission shaft 30, mounted in a radial rack 16 and executed by the PTO on the shafts of the rotor ND and VD, are installed in front of the camera 10.

The separator 5 separates the primary flow from the secondary flow S. the separator is formed of two annular walls 5A and 5b, through which radial strut 16, in this case, the path of the primary beam has a smaller cross-section compared with the cross section contour of the secondary stream.

Figure 3 shows the crankcase 100, are presented in figure 2, in section along a vertical plane passing through the axis of the engine and the lower rack 16. This figure shows a 16 hour, shell 2, the hub 1 and the walls 5A and 5b of the separator inside the crankcase. The primary flow is shown by arrows R; secondary flow is shown by arrows S.

Hollow strut 16 is formed by two radial parts, continuing each other: the first part C1 passes through the primary flow P, the second part C2 passes through the secondary flow S. They have a corresponding geometric shape. So, part C1 of the rack is narrower than the portion C2. This difference in shape is more obvious in figure 4 and 5, where the radial strut 16 is shown in the cut.

The geometric shape of the transmission shaft 30 is chosen appropriate, while dia is the ETP of the shaft 30 more in part C2 radial rack 16, than in part C1.

The internal volume of the radial rack 16 is formed of a single compartment that allows you to transport lubricating fluid such as oil. Lubricating fluid is in direct contact with the walls of the rack 16 and with the outer surface of the transmission shaft 30. Radial strut 16 establishes communication between the anterior chamber 10 and the frame 20 drives the auxiliary equipment for the lubrication of bearings 6, to limit, thus, wear and heat.

In the present example, the internal volume of the radial rack 16 removes the oil coming from the front camera 10, in box 20 of engine accessory drives.

As shown in figure 3, the transmission shaft 30, mounted in the compartment filled with lubricating fluid passes through the holes made respectively in the transverse surfaces 12, 22 of the inner hub 1 and the outer cylindrical shell 2 at the ends of the shaft 30 mounted respectively in the guide bearings 13, 23, fixed in the anterior chamber 10 and in box 20 of engine accessory drives.

The clearances between the gear shaft 30 and the openings in the transverse walls 12, 22 is accomplished calibrated to regulate the flow of lubricating fluid between the front camera 10, the inner radial displacement of the rack 16 and is orobko 20 drives the auxiliary equipment. This can be done at the time of manufacture with the use of the appropriate class finish, equivalently, in particular, the class of finish oil chamber. In addition, it is not so critical, given that the transmission shaft is no intermediate support bearing.

Reinforcing ribs 40, made in the longitudinal direction and the inside radial 16 hours, allow to increase the rigidity of the rack 16. Preferably reinforcing rib 40 is made of openwork, in order not to increase the mass of the radial rack 16, but does not reduce with the rigidity of the Assembly.

Radial strut 16 may also provide communication between the anterior chamber 10 containing bearings shafts 6 ND and VD, and an oil reservoir, located in box 20 drives the auxiliary equipment, to ensure the removal of that power or generate oil pressure in the anterior chamber 10.

In the radial rack can also install other types of auxiliary equipment, such as cables, pipelines or additional shafts.

1. Intermediate crankcase bypass turbofan engine containing at least one annular partition separating the gas stream into two annular concentric flow, primary and secondary, respectively, while between the inner with what Epica and outer cylindrical rings, there are many radial struts, at least one of which is hollow and contains the first part passing through the primary flow, the second part passing through the secondary flow while in the above-mentioned radial rack is mounted for rotation radial transmission shaft accessory drive, with the first end of the transmission shaft passes through the inner hub and the second end passes through the outer cylindrical shell, wherein the internal volume of the radial rack consists of a single compartment, which houses the transmission shaft and which forms a channel for lubricant.

2. Intermediate crankcase according to claim 1, in which between the ends of the transmission shaft and the holes formed in the inner hub and an outer cylindrical shell, respectively, leave calibrated gaps.

3. Intermediate crankcase according to claim 1, in which the first mentioned portion of the rack is shorter than said second part.

4. Intermediate crankcase according to claim 3, in which the radial part of the rack passing through the secondary flow includes longitudinal reinforcing ribs.

5. Intermediate crankcase according to claim 4, in which reinforcing ribs made with.

6. Intermediate crankcase according to claim 1, in which the transmission shaft is made mon the block.

7. Turbojet engine, containing a camera with bearings, a box of engine accessory drives and intermediate crankcase according to claim 1, mentioned radial strut which provides communication between the said chamber and the said gearbox auxiliary units.

8. Turbojet engine according to claim 7, in which box accessory drivers contains the oil reservoir which communicates with the chamber via a radial rack.



 

Same patents:

FIELD: engines and pumps.

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11 cl, 5 dwg

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16 cl, 6 dwg

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14 cl, 3 dwg

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2 cl, 3 dwg

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3 cl, 1 dwg

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2 dwg

FIELD: power engineering.

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2 cl, 3 dwg

FIELD: machine building.

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3 cl, 3 dwg

FIELD: mechanical engineering; aircraft engineering.

SUBSTANCE: invention relates to antifriction bearing with lubricating film exposed to pressure and acting according to "forced-out film" type. Proposed antifriction bearing of turbomachine used to form rotary support of first shaft 4 relative to second shaft 6 contains great number of solid of revolution 12 fitted between inner ring holder 14 installed on second shaft 6 and outer ring holder 16 installed on first shaft 4. Inner surface of holder 16 and outer surface of holder 14 limit ring space in between. Bearing contains oil film 18 formed at level of ring surface of contact between holder 16 and shaft 4 and limited from sides by sealing rings 20, 22. Bearing contains also one feed channel 34 passing through holder 14. Channel 34 communicates with oil feed circuit and it comes to level of inner race of solids of revolution 12 to provide their lubrication, and at least one additional channel 38 passing through holder 14 is provided. Channel 38 communicates with oil feed circuit and terminates outside relative to inner race to feed oil through holder 16 to oil film 18 under action of centrifugal force created by rotation of shaft 6. Holder 16 is provided with ring flange 42 forming radial projection pointed inwards ring space. Flange 42 is provided with at least one feed channel 40 beginning mainly opposite to channel 38 and terminating at level of oil film 18.

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6 cl, 2 dwg

FIELD: lubrication of telemetering-system power generator.

SUBSTANCE: proposed lubricating system of telemetering-system power generator has priming device on its front end, space filled with lubricant disposed between external rotor incorporating at least one turbine casing installed through front and rear bearings on stator provided with shaft, and lubricant thermal expansion device made in the form of spring-loaded piston mounted inside rotor for axial displacement; piston is installed between turbine casing and bushing, and the latter is installed and secured in position within turbine casing; end-seal pair contacts bushing but-end. One of parts incorporated in end-seal pair has slots and round holes and other part has mating projections with longitudinal slots opposing mentioned holes; junction pins are passed through these slots and holes. Springs are installed between two parts of end seal. Bushing is locked by end projections in slots of intermediate ring whose outer surface carries pin that enters slit in turbine casing. Through slots are made on bushing end. Adjusting ring that functions to vary pressure in end seal is inserted between rotor and front bearing.

EFFECT: enhanced operating reliability of end-seal pair and lubricant thermal expansion device.

16 cl, 3 dwg

FIELD: heat power engineering.

SUBSTANCE: invention can be used in turboplant of power-and-heating plants, thermal and nuclear power stations. Proposed turboplant contains low-, medium-, and high-pressure cylinders with branch pipes and pipelines to deliver and let out steam with intermediate vertical supports connected to cylinders, rotors and feet of housings. Feet of housings rest on movable bearings sliding along longitudinal key joints relative to fixed foundation frames installed on cross-bars of foundation. Pipelines to deliver and let out steam, shells of heaters, regenerative and heating extractions and valves are provided with limited displacement supports. Each limited displacement support is made guide and turnable in critical directions within tolerable limits. Displacement is limited by thrust spring unit, and turning is limited by rolls with locks. Base of turboplant support is made movable with possibility of turning and limited displacement. Base of support is installed inside fixed housing made in form of parallelepiped on rolls with spacer strips in number of two, minimum. Rolls with spacer strips are installed from below relative to movable base and move along rolling guides. Turning of movable base is limited from side by rotating rolls with locks, two locks for each side surface minimum. Longitudinal displacement of base of support is limited by thrust spring unit.

EFFECT: improved reliability and increased service life of turboplant and its foundation.

2 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: bearing support for retention of the shaft in a jet turbine engine in the required direction includes an annular part made from material with shape memory effect, which maintains the original form when the imposed load remains below the threshold value and which is deformed after energy absorption when the imposed load becomes equal at least to the threshold value; at that, the annular part is capable of taking again at least approximately its original form when imposed load becomes lower than threshold value.

EFFECT: providing the possibility of performing repeated shaft alignment after disconnection of guide bearings from low pressure compressor shaft after the jet turbine engine is set to autorotation mode so that destruction of the other guide bearing can be avoided and jet turbine engine structure can be maintained.

11 cl, 4 dwg

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