Fitting of agb at turbojet housing blower mid housing

FIELD: engines and pumps.

SUBSTANCE: mid housing (20) of turbojet blower compartment (Cs) comprises the following components: Shell ring (22), circular web (24), suspension beam (28) and auxiliary gearbox (30). Shell ring (22) is centred in gas turbine engine lengthwise axis (X-X). Circular web (24) is centred in engine lengthwise axis and located opposite shell ring downstream side. Suspension beam (28) is secured to said web to extend in flow direction, parallel with engine lengthwise axis. AGB (30) swivels on said beam and comprises upstream lateral side (30b) axially spaced from the web, downstream lateral side (30a) opposite said upstream lateral side. Besides, it comprises multiple auxiliary hardware (32) arranged opposite downstream lateral side and along engine lengthwise axis.

EFFECT: possibility to fit AGB in aircraft central compartment.

8 cl, 2 dwg

 

Background of invention

The present invention generally relates to the field of installation of the drive unit aggregations on a turbojet engine.

In turbine engine components, such as pumps for the production of hydraulic energy, fuel and perform lubrication, and electrical generators to produce electrical energy and so on, are grouped together in the node, commonly referred to as a gearbox units (KPA). This site usually contains one or more gears, driven in rotation by the power taken from the shaft turbojet engine, and connected to various units.

In turbojet engines family CFM KPA usually installed in the zone or area of the fan compartment. Rather, they are suspended from the flanges formed on the metal holding the blades of the case mentioned of the fan compartment.

However, in an attempt to reduce the weight of the holding section of the fan compartments are increasingly made from composite material. Unfortunately, it is difficult to manufacture the flanges providing attaching KPA to such bodies made of composite material.

In addition, manufacturers of aircraft require turbojet engines were given increasingly high levels of electrical is Amnesty, that usually leads to the installation KPA two large electric generators. As a result, when mounting KPA in the area of the fan compartment of the turbojet engine nacelle expand in accordance with the aforementioned KPA in order to reduce the area of the front surface of the nacelle. However, the aforementioned extension leads to thermodynamic effects that have a negative impact on performance.

To solve these problems of the known installation KPA in the Central Bay, or "center" of the turbojet engine and, more specifically around the high pressure compressor of the turbojet engine. However, this type of installation leads to technical difficulties. In particular, when installing a significant load on the compressor casing of a high pressure increases the risk characteristics of the above-mentioned case due to the phenomenon of ovalization of the casing (okalizacja has a correspondingly greater effect with a small diameter of the compressor housing). In addition, the presence of air tubing to bleed the air upstream from the compressor high pressure at certain stages of the flight limits the ability to attach KPA to the components of the compartment centre otherwise than to the body of the high-pressure compressor.

Objective and summary of the invention

Thus, the main purpose of this breath is retene is to overcome these disadvantages by providing a method of installing KPA in Bay center turbojet engine without degradation of the high pressure compressor of the turbojet engine.

This goal is achieved through the intermediate casing of the fan compartment turbojet engine, comprising: a shell centered on the longitudinal axis of the gas turbine engine,

ring cheek, centered on the longitudinal axis of the gas turbine engine and installed located opposite the downstream side of the shell,

suspension beam attached to the cheek and extending downstream parallel to the longitudinal axis of the gas turbine engine, and

- KPA suspended on the beam, and containing above a stream in the side, axially spatially separated from the cheeks, below the downstream side, located opposite upstream side, and many units installed across its located downstream side and distributed relative to the longitudinal axis of the gas turbine engine.

The intermediate casing turbojet engine is located between the low-pressure compressor and high pressure compressor. In addition, KPA, which is suspended on a beam attached to the cheek of the intermediate casing may be placed around the high pressure compressor of the turbojet engine, without being directly attached to it. This eliminates any risk-reducing nature of the stick housing of the compressor high pressure due to the ovalization. In addition, the installation KPA in accordance with the invention, allows you to push the KPA from the cheeks of the intermediate casing in such a way as to leave space for the passage of air tubing to bleed the air upstream from the high pressure compressor.

In a preferred embodiment, KPA attached at one end to the beam and the opposite end of the plug, which is attached to the cheek, the housing further comprises a fuel site, attached one end to the fork cheeks, and the opposite end of the beam. Thus, adding fuel site provides education together with KPA vicious circle centered on the longitudinal axis of the turbojet engine, which facilitates balancing weights in an optimal way on the said longitudinal axis. In addition, each KPA can be removed independently of the others, which facilitates its maintenance.

In this case, the fuel site may contain above a stream in the side, axially spatially separated from the cheeks, below the downstream side, located opposite upstream side, and many units of fuel and equipment installed on the contrary it is located downstream side.

Preferably, the BAC Ni is sustained fashion contains the transmission node, set opposite its located up stream side.

It is also preferred that the housing further comprises at least one axial thrust efforts, attached at one end to the cheek, and the opposite end is located upstream side of the KPA.

Accessories KPA may contain: at least one electrical generator to power the plane with electric power, the AC generator to supply electricity to the electrical equipment of the gas turbine engine, the starter motor to start the gas turbine engine, at least one hydraulic pump to power the aircraft hydraulic energy, fuel pump and oil pump.

The invention also relates to fan turbojet engine compartment, containing the retaining body, centered on the longitudinal axis of the gas turbine engine, and above the intermediate casing attached to the holding body.

The invention additionally relates to a turbojet engine, comprising the above-described intermediate casing.

Brief description of drawings

Other properties and advantages of the present invention will be clear from the following descriptions made with reference to the accompanying features of the LM, showing has not restrictive option implementation. In the drawings:

Fig.1 is a side view of the turbojet engine equipped with intermediate casing according to the invention, and

Fig.2 is a view in section along the line II-II shown in Fig.1.

Detailed description of option exercise

Fig.1 is a side view showing a turbofan engine 10, which is the turbojet engine double-shaft double-circuit type with intermediate casing according to the invention. Naturally the scope of the invention extends to other types of turbine engines.

It is known that such a turbojet engine 10 is located upstream compartment, which houses the fan, also called the fan compartment Cs and located downstream compartment, which houses the rest of turbojet engine, also called the "hub" of Cc or Central compartment.

More precisely drawer Cs includes holding the blade body 12 formed by the shell 14, preferably made of composite material), centered on the longitudinal axis X-X of the turbojet engine and located at both of its ends with flanges, namely located upstream flange 16 and on th is m downstream flange 18.

Drawer also includes the intermediate casing 20 attached to a located downstream flange 18 holding the housing 12. Mentioned intermediate casing is formed of a metal shell 22, centered on the longitudinal axis X-X of the turbojet engine, and an annular cheek 24 centered on the longitudinal axis X-X and which is located opposite the downstream side of the shell 22 (Fig.2).

In addition, the turbofan engine 10 suspended from the wing of the aircraft (not shown) through the pylon 26, these pylon is connected with a turbojet engine with an overhead beam 28 that is attached to the cheek 24 of the intermediate casing 20. This suspension beam extends downstream parallel to the longitudinal axis X-X of the turbojet engine.

According to the invention provides the use of the above suspension beams 28, which is designed for attachment pylon 26, for hanging the box drive units (KPA) turbojet engine, with KPA place, or more precisely, around the high pressure compressor of the turbojet engine.

KPA includes located downstream side 30a, which is essentially flat, and located upstream side 30b, which is essentially flat is located opposite downstream side. The presence of suspended beams provides axial spatial separation KPA from the cheeks of the intermediate casing. Thus, the space left between these two elements, allows to pass through it of the air tube 31 to bleed the air upstream from the high pressure compressor of the turbojet engine.

In addition, KPA 30 includes one or more gears (not shown) driven in rotation by means of power take-off shaft turbojet engine. Many units are installed opposite situated downstream side 30a KPA 30, and each of them represents a drive shaft connected with one of the gears KPA. These drive shafts (not shown in the drawings) lie in a direction essentially parallel to the longitudinal axis X-X.

Among these units, there are two electric generator 32 to power the aircraft with electrical energy, the generator 34 AC to supply electricity to the electrical equipment of the gas turbine engine starter (not shown) to start the gas turbine engine, a hydraulic pump (not shown) to power the aircraft hydraulic energy, fuel pump 36 and the lubricating pump 38. Of course on the KPA can be installed in different units, different from the above.

the moreover, KPA 30 includes a transmission node 40 (Fig.2) through which passes the shaft receiving power from the shaft turbojet engine that drives the various units. Mentioned transmission node 40 is preferably set located opposite the upstream side 30b KPA.

One of its ends KPA 30 is attached to the outboard-powered 44, while the mentioned suspension rod attached to the transverse rod 46, forming a cross member and attached to the outboard beam 28. On the opposite end of the KPA 30 is connected with a plug 48 that is attached to the cheek 24 of the intermediate casing 20.

In a particularly preferred embodiment, the intermediate casing additionally comprises a fuel node 50, attached at one end to the plug 48 cheeks 24 and the opposite end to the outboard beam 28 (through the hanging rod 52 attached to the transverse bar 46).

Fuel site contains 50 located upstream side, axially spatially separated from the cheeks, below the downstream side, located opposite upstream side, and many units of fuel equipment located opposite its downstream side. For example, this equipment comprises a control unit 54 to control when odnymi the servo-valves, a group of exchangers and fuel/oil filters 56a and 56b and the valve 58 fuel metering.

Thus, KPA 30 and the fuel node 50 together form an Assembly that represents a vicious circle centered on the longitudinal axis X-X of the turbojet engine. Units/equipment this Assembly is placed on the said longitudinal axis X-X and are located in a compartment of the center of the turbojet engine and, more specifically around the high-pressure compressor. Thus, it can be optimally balance the weight on the said longitudinal axis X-X. in Addition, each node (KPA or fuel site 50) can be removed independently from each other, which facilitates their maintenance.

As shown in Fig.1, thrust 60 axial efforts can be attached by one of their ends to the cheek 24 of the intermediate casing, and the opposite ends to located up stream side 30b KPA 30.

In the above description of the intermediate casing of the invention KPA suspended on an overhead beam, which is usually used to attach the pylon. Such an implementation option provides the advantage that the suspension beam for attaching the pylon is designed in size to resist loads which exceed the load from the suspension KPA. In addition, since the aforementioned suspension beam is already available, change its shape has minor effects on the total weight of the turbojet engine.

However, some turbojet engines have a different system mounting pylon, in which there is no suspension beam attached to the intermediate casing of the fan compartment. Of course with this configuration, it is obvious that such suspension beam could be installed on the cheek intermediate casing for hanging KPA installed in accordance with the invention.

1. The intermediate casing for the fan of the turbojet engine compartment containing:
- shell centered on the longitudinal axis of the gas turbine engine,
ring cheek, centered on the longitudinal axis of the gas turbine engine and installed located opposite the downstream side of the shell,
suspension beam attached to the cheek and extending downstream parallel to the longitudinal axis of the gas turbine engine, and
- box of actuator units, suspended on the beam, and containing above a stream in the side, axially spatially separated from the cheeks, below the downstream side, located opposite upstream side, as well as many units installed across its located downstream side toronyi distributed relative to the longitudinal axis of the gas turbine engine.

2. The case under item 1, in which the box drive units (KPA) attached at one end to the beam and the opposite end of the plug that is attached to the cheek, the housing further comprises a fuel site, attached one end to the fork cheeks, and the opposite end to a beam.

3. Building on p. 2, in which the fuel site contains located upstream side, axially spatially separated from the cheeks, below the downstream side, located opposite upstream side, as well as many units of fuel and equipment installed on the contrary it is located downstream side.

4. The case under item 1, in which the CPA further comprises a transmission node, set opposite its located up stream side.

5. The case under item 1, additionally containing at least one axial thrust efforts, attached at one end to the cheek, and the opposite end is located upstream side of the KPA.

6. The case under item 1, in which the units contain at least one electric generator to power the plane with electric power, the AC generator to supply electricity to the electrical equipment of the gas turbine engine, a starter for starting gasoturbinnaya, at least one hydraulic pump to power the aircraft hydraulic energy, fuel pump and oil pump.

7. Fan turbojet engine compartment, containing the retaining body, centered on the longitudinal axis of the gas turbine engine, and an intermediate body under item 1, with the intermediate casing is attached to the holding body.

8. Turbojet engine comprising an intermediate body under item 1.



 

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