Double-flow turbojet engine with the intermediate jacket, with the drive shaft of transfer gearbox for turbojet engine accessory drive

FIELD: turbojet engine.

SUBSTANCE: double-flow turbojet engine contains the intermediate jacket, with installed drive shaft of transfer gearbox in its radial arm designed to auxiliary drives. The drive shaft of output transfer gearbox is connected on its first end with the mechanical transfer mechanism placed on the drive shaft of the turbojet engine, and on the second end with the mechanical transmission to the abovementioned gearbox. The drive shaft of output transfer gearbox has a conic gearwheel between two ends of this shaft and allows providing mechanical linkage with additional auxiliary equipment. The drive shaft of output transfer gearbox in combination with the abovementioned gearwheel is encased forming an oil circuit, sealed in relation to the radial arm.

EFFECT: allows limiting a inflammable area at the expense oil leak elimination.

16 cl, 6 dwg

 

The present invention relates to the field of multi-stage and multistage gas turbine engines, in particular to the field of two-stage and turbojet engines. This invention relates to the mounting of auxiliary equipment and mechanical transmission between these accessories and the shaft of the engine.

For driving the auxiliary equipment installed on the engine, such as electric generators, oil pumps or fuel pumps necessary for the functioning of the engine or for the operation of the aircraft on which the engine is installed, usually select the required power on the main shaft of the engine. Two-stage turbofan engine includes two coaxially arranged shaft, and one of these shafts, or the so-called shaft low pressure, or per BP, connects the low-pressure compressor with a low-pressure turbine and forms a system of cascade low pressure BP and the other shaft, or the so-called shaft high pressure, or shaft HP, connects the high-pressure compressor to the high-pressure turbine and forms a system of cascade high pressure HP. In this engine the transmission of power to the auxiliary equipment is usually provided by means of radial location is tion of the countershaft, placed in the bracket of the intermediate casing, and one end of the transmission shaft includes a conical gear interacting with a pinion rigidly connected with the cascade of high pressure. The other end of the countershaft is connected mechanically with a manual gearbox, containing a lot of the gears and forming a support for the auxiliary units, while bringing these units in motion. In the case when the turbojet engine is a dual circuit, mentioned radial transmission shaft passes through two channels of movement, respectively, of the primary stream and the secondary stream, since the gear reducer driving auxiliary units, also referred to as AGB ("accessory gear box"), installed on the fan shroud, which creates a secondary thread (FR 2882096).

In the process of improvement of engines and conditions of their use was prompted to install additional equipment on the casing of the primary flow channel, which is in toothed engagement with a radial shaft driving auxiliary units between the two ends of this shaft. Such equipment can be formed, for example, engine that allows you to move the radial transmission shaft in addition to the cascade high pressure HP. the actual, this addition is useful in the case where the engine design includes a major power during operation of the engine in idling conditions in order to provide a reduction in the movement of some auxiliary units, such as electric generators. When the engine is in idling conditions the cascade high pressure HP is unable to issue a sufficient number of the required power.

The present invention is an improvement over prior art engines.

The present invention relates to the installation of additional equipment or unit on the motor housing in some intermediate position between the two ends of the radial transmission shaft or drive shaft gear reducer PTO, used to drive auxiliary units, as well as to the relative location of this accessory with respect to the radial transmission shaft.

The task is solved in that in accordance with the invention turbojet engine includes an intermediate casing with the drive shaft gear reducer PTO designed for accessory drive installed in the radial sleeve this intermediate casing, and the said drive shaft subca the CSOs gearbox PTO is connected at its first end with a gear reduction means, placed on the shaft of this turbojet engine, and is connected at its second end with a mechanical means for transmitting movement to said gear, and includes a bevel gear located between the two ends of this shaft and provides a mechanical connection with optional accessories, and differs in that the drive shaft of the gear reducer PTO together with the previously mentioned gear is enclosed in a casing forming an oil path that is sealed with respect to said sleeve.

The design of the drive shaft gear reducer in accordance with the proposed invention eliminates oil leakage and limit thus the fire zone. This circumstance is particularly relevant in the case when the design of the intermediate casing contains an attached outer shell, and the number of parts connected by bolted joints, usually increases the risk of oil leakage.

Preferably, the said shell contained a casing for the gears and two case intended for parts of the shaft, located on either side of this gear.

The invention applies, in particular, in the case where the above-mentioned driven shaft gear reducer selection power sostoi the three cylindrical elements, inserted one into the other, and the first cylindrical element of this shaft is mounted mentioned gear, and the other two cylindrical element of this shaft continue this first cylindrical element with one and with his other hand.

Preferably also for the accessories contained drive axis, interacting with said gear shaft, and was carried out in such a way as to form together with this gear modular system. This solution is particularly preferred because it allows you to simplify the installation of equipment in the factory, as well as to facilitate its subsequent maintenance and allows you to have interchangeable equipment. Mounting and fine adjustment of the bevel gear pair can be thus carried out accurately enough out of this turbojet engine, space is limited and usually cluttered various structural elements. When mounting on a turbojet engine can only be inserted one into another of different cylindrical elements of this radial drive shaft. This operation does not require the use of precision equipment.

Preferably, modular accessories contain bearings which, which by bearings mounted mentioned gear.

It is preferable that the above-mentioned gear housed in the space of radial sleeve, which forms the separation between the channel of movement of the primary stream and the channel of movement of the secondary stream.

It is preferable that the above-mentioned casing, in which is mentioned the gear was placed in the above-mentioned space radial sleeves.

Below is a detailed description of non-restrictive variant implementation of the invention with reference to figures, in which:

figure 1 is a General schematic view in axial section of double-loop and two-stage turbojet engine, which can be applied to the present invention,

figure 2 is a schematic view of the intermediate casing in the axial incision made through the radial sleeve, in which is placed a shaft driving the gear reducer AGB, with additional auxiliary equipment in accordance with the invention,

figure 3-6 schematically depict the sequence of installation of the shaft in accordance with the invention, containing additional accessories.

Figure 1 is a schematic circuit and on whiskey turbojet engine with its various major components. This engine contains the first shaft 3 connecting, as can be seen in the left part of the figure, the fan rotor 5 and the first stage 7 of the compressor low-pressure turbine 9; this system forms a cascade of low pressure BP. Located coaxially with the first shaft, the second shaft 11 in the form of drum associates degree 13 high pressure compressor with the turbine 15 high pressure; this system forms a cascade of high pressure HP together with the combustion chamber 17. Mentioned shaft 3 is held in the front of the downstream side by means of a support bearing 3A mounted on the casing 19, which is called the intermediate casing, and is held in its rear flow side by means of a support bearing 3C mounted on the exhaust casing 21. The second shaft 11 cascade high pressure HP is retained in this case by means of a support bearing 3b mounted on the intermediate casing 19, and the rear part is held by means of the shaft 3 through megaleg bearing 3d.

Intermediate casing is formed by a sleeve 19a, retaining bearings 3A and 3b, the outer shell 19b equipped with front suspension means on the aircraft and holding the fan shroud, and radial sleeves 19s connecting sleeve 19a with a drum 19b. This intermediate casing formed of at least frequent is the rule, a molded part, which, if necessary, fixed radial sleeves. Auxiliary units, such as electric generators and fuel or oil pumps are installed in a known manner on the housing 23, which in the art is denoted by the abbreviation AGB. This gearbox is installed outside of the fan shroud in place that allows access for maintenance. The drive gear gear mechanically connected to the motor shaft by means of radial shaft 25 of the drive gear reducer PTO, which is located in the radial sleeve 19s intermediate casing. This shaft is connected with the first bevel gear located on its inner radial end. This gear is in mesh with a bevel gear fixed to the cascade high pressure HP. The shaft 25 is also connected with the second gear at its outer radial end which is engaged with the input shaft system gear reducer AGB.

In the operation of this engine sucks air through a fan that provides compression and forms a primary flow passing through the compression stage, a combustion chamber and stage of the turbine, and a secondary flow, which is thrown away at at the osfera, passing a circuitous route around the combustion chamber. Turbines operate the compression means through the shaft of the low pressure BP and the shaft of the high pressure HP, respectively.

It has already been proposed to place additional accessories in the space formed in the casing, located between these two streams, primary and secondary. This equipment is in accordance with this example implementation is an additional engine, which drives the shaft 25 of the drive gear reducer PTO in the case when cascade high pressure HP is not enough. In the field of aircraft engines this is the case when the number of ancillary driven units and required for their work capacity are significant when the engine is in idling conditions. Such auxiliary engine can represent, for example, an air turbine, fed by gases of the said primary stream.

In addition to the discussed embodiment, the invention is applicable to any additional accessories, such as the slave or the master unit, which is placed in this space.

The problem faced in this case, partly connected with smask the th, requiring oil consumption far exceeding the existing capacity for the drive shaft gear reducer selection power for the accessory drive. The present invention relates to the technical solution that allows you to resolve this issue.

Figure 2 presents a partial schematic view in axial section of the engine at the level of the aforementioned drive shaft gear reducer PTO according to the invention.

In this figure parts corresponding to the parts presented in figure 1, are denoted by the same digital items, but increased by 100. So here you can see the intermediate casing 119, in the radial bracket s which houses the shaft 125 drives the gear reducer PTO, used to drive auxiliary equipment, not shown in figure 2. The shaft 125 passes through the cowling 119b intermediate casing and its outer radial end mechanically connected, for example, by means of a splined connection with a pair of bevel gears, which are not shown in this figure.

The sleeve s is hollow and is formed in the radial direction in three different parts: s, s and s.

Part C, profiled in aerodynamic terms, passes through the channel of movement of the primary beam P, one side of which VI is the et of the compressor 107 low pressure BP, and part of the compressor 113 high pressure HP, on the other hand. Part s sleeves s adjoins the sleeve a intermediate casing.

Radial sleeve s contains part is passing through the channel of movement of the secondary stream S. This part C is adjacent to the ring 119b.

The said sleeve also contains part is located between the two above-mentioned first part. This part restricts the annular space, which continues on the one hand, the toe separation between the primary stream and the secondary stream, and on the other hand, he continues annular space 129 located between these two threads.

Located in the hub a thrust bearing 103 holds the shaft 103 cascade low pressure BP, and thrust bearing 103b holds the pin 111, which forms a front downstream end of the compressor 113 cascade high pressure HP.

The shaft 125 is placed in the specified radial sleeve intermediate casing. The shaft 125 is composed of three elements: 125, 125b and 125C. The first Central element 125 has a cylindrical shape, is hollow and is rigidly connected with the bevel gear a. The second element 125b performed inserted with the inner radial direction side in the above-mentioned first element 125 a and held therein by means of splined connection. At its inner end it is the element connected using spline connection with a pair of bevel gears 126, located in engagement with the pin 111 cascade high pressure HP. Thus, the element 125b is driven by means of cascade high pressure HP.

The third element 125C performed inserted from the outside in the radial direction in the above-mentioned first element 125 a and held therein by means of splined connection. As can be seen from the drawing, the radial end of the element is not visible on this figure. He is mechanically connected through a pair of bevel gears to the input shaft of the gearbox AGB. Thus, rotational movement of cascade high pressure HP is transferred via a transfer means formed by a pair of bevel gears 126 and the shaft 125, the input shaft of the gearbox AGB.

Optional accessories 128 is placed in the space formed by the motor housing, which is positioned between the channel of movement of the primary stream and the channel of movement of the secondary flow. This accessory contains the axis a motion, ending with a bevel gear a. Accessories 128 secured with screw connection on side wall part s radial sleeves s, which continues the above-mentioned annular space.

As such equipment may, for example, to perform the engine air t is rbine, hydraulic motor designed to move when necessary, the shaft 125. It can also be an additional slave unit driven shaft 125.

The supporting casing 128b is rigidly connected with the casing of the equipment 128. This casing 128b holds a Central element 125 of the shaft 125 by means of two bearings 128b1 and 128b2 so that bevel gear I was engaged with the bevel gear a element 125 to transfer rotational motion from one element to another. For ease of Assembly of the supporting casing 128b includes a cover 128b', on which is mounted the bearing 128b2.

Accessories 128 together with the axis a, a supporting casing 128b and the element shaft 125 125 together form module 130, a single in the sense that the system of this module can be assembled separately and installed on the turbojet engine in the form of a block, as will be discussed in more detail below.

The module 130 associated with the shaft 125, isolated from the inner space of the sleeve s using shell 131.

This shell is formed by a casing a and two covers 131b and s. The casing a covers the supporting casing 128b hardware element 128 and 125, which he holds. This shell contains three holes, one of which is intended for the passage of equipment 128, and the other VA are designed for the passage respectively of the elements 125b and 125C of the shaft.

Case 131b covers the element 125b of the shaft 125, and the case s covers the element 125C of the shaft. Appropriate sealing gaskets provide a seal between the casing a and two covers 131b and s. In addition, the sealing strip is provided on the other two ends of these two cases.

The casing 128b fixed by a bolt connection on the wall of the sleeve s.

This shell has the opportunity to sum up the oil required for lubrication of the equipment and elements of the mechanical transmission, using a path that does not interact with radial sleeves of the intermediate casing of the engine. So, for example, oil that provides lubrication for the pair of bevel gears a and a going into the space made between the elements 125b and 125C of the shaft and covers 131b and s respectively, for re-use.

For more efficient reuse of oil a special device can be installed at the lowest point of the casing a to be addressed directly in the path of the recovery engine, the predominant part of the oil used for lubrication of tapered pair of gears and bearings. This device will prevent the gear AGB of the oil flow, which may be contaminated shavings coming from the mechanical components shall now mentioned module.

Further installation of the above system will be described in more detail with reference to figure 3-6.

Figure 3 schematically shows an Assembly module 130. The supporting casing 128b attached to the equipment 128, axis a which is not shown in this figure. Then enter the element 125 a gear shaft 125 and close the cover lid 128b'. The bearings between the element 125 and the supporting casing 128b this figure is not shown.

Figure 4 schematically shows an assembled module 130. It seems clear that such an operation can be performed in the workshop, different from the Assembly shops engine, or from a supplier. This module can be supplied assembled, which is a definite advantage, as the delicate operation of adjusting a pair of bevel gears must be performed by qualified personnel using specialized technological tools.

Figure 5 schematically shows an installation of casing a shell 131 in the inner cavity of the intermediate casing 119 of the engine in part C. Radial sleeves s not represented on this figure. The next step is introducing the outside of the cover 131b, equipped with its gaskets, through the radial holes of the casing a, and then cover s equipped with their gaskets.

As can be seen on IG, enter the module 130 in the casing a through the axial hole of the intermediate casing 119 after installation of the cover 131b. The module 130 mounted on a prescribed place, it is not possible to cover 131b to get out of his bed. Then fix using bolted connection module 130 on the radial wall of the casing 119, and then complete the installation by installing two shaft element, the first element 125b, and then the element 125C.

1. Turbofan engine with an intermediate casing with the drive shaft gear reducer PTO designed for accessory drive installed in the radial sleeve this intermediate casing, and the said drive shaft of the gear reducer PTO is connected at its first end with a gear reduction means, placed on the control shaft turbojet engine, is connected at its second end with a mechanical means for transmitting movement to said gear and contains a bevel gear located between these two ends of this shaft and provides a mechanical connection with optional accessories, characterized in that the drive shaft of the gear reducer PTO together with the said gear is enclosed in a casing forming an oil path sealed by the compared to the said sleeve.

2. Turbojet engine according to claim 1, in which said casing includes a casing intended for gear, and two case intended for parts drive shaft gear reducer PTO, located on either side of this gear.

3. Turbojet engine according to claim 1, in which the drive shaft of the gear reducer PTO consists of three cylindrical elements, inserted one into the other, and the first cylindrical element of this shaft is mounted mentioned gear, and the other two cylindrical element of this shaft continue this first cylindrical element with one and with his other hand.

4. Turbojet engine according to claim 2, in which the drive shaft of the gear reducer PTO consists of three cylindrical parts, inserted one into the other, and the first cylindrical element of this shaft is rigidly mounted mentioned gear, and the other two cylindrical element of this shaft continue this first cylindrical element with one and with his other hand.

5. Turbojet engine according to claim 3, in which the auxiliary equipment includes the axis of the propulsion of interacting with the said gear drive shaft gear reducer PTO and forming together with this gear modular system.

6. arboreality engine according to claim 4, which accessories contains the axis of the propulsion of interacting with the said gear drive shaft gear reducer PTO and forming together with this gear modular system.

7. Turbojet engine according to claim 5, in which the accessory comprises a support on which said gear is mounted by means of bearings.

8. Turbojet engine according to claim 6, in which the accessory comprises a support on which said gear is mounted by means of bearings.

9. Turbojet engine according to claim 5, in which said gear is placed in the space of radial sleeve forming the separation of the primary stream and the secondary stream.

10. Turbojet engine according to claim 6, in which said gear is placed in the space of radial sleeve forming the separation of the primary stream and the secondary stream.

11. Turbojet engine according to claim 7, in which said gear is placed in the space of radial sleeve forming the separation of the primary stream and the secondary stream.

12. Turbojet engine according to claim 8, in which said gear is placed in the space of radial sleeve forming the separation of the primary stream and the secondary stream.

13. Turbojet engine pop, in which said casing includes a casing designed for gear and placed in the above-mentioned space radial sleeves, and two case intended for items of the shaft, located on either side of this gear.

14. Turbojet engine of claim 10 in which the said casing, in which is mentioned gear is placed in the above-mentioned space radial sleeves.

15. Turbojet engine according to claim 11, in which said casing includes a casing designed for gear and placed in the above-mentioned space radial sleeves, and two case intended for items of the shaft, located on either side of this gear.

16. Turbojet engine according to item 12, in which the said casing, in which is mentioned gear is placed in the above-mentioned radial space of the sleeve.



 

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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

The invention relates to the field of turbine construction, such as control systems seals and the oil supply device of turboexpanders

Turbogenerator // 2186225
The invention relates to the field of energy

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

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