An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.
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1. An engine cowling of an aircraft gas turbine, comprising:
a front area, and
a rear area that is displaceable in an axial direction,
a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators,
wherein the rear area is directly mounted to, and supported by, the second ends of the plurality of thrust reversal actuators,
wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area.
7. An engine cowling of an aircraft gas turbine, comprising:
a front area, and
a rear area that is displaceable in an axial direction,
a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators,
wherein the rear area is mounted to, and supported by, the second ends of the plurality of thrust reversal actuators,
wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area, and
rails extending in the axial direction, and arranged only in an upper area of the engine cowling.
8. An engine cowling of an aircraft gas turbine, comprising:
a front area, and
a rear area that is displaceable in an axial direction,
a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators,
wherein the rear area is mounted to, and supported by, the second ends of the plurality of thrust reversal actuators,
wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area,
wherein mounting positions of the second ends on the rear area are fixed in relationship to one another.
2. The engine cowling according to
3. The engine cowling according to
4. The engine cowling according to
5. The engine cowling according to
6. The engine cowling according to
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This application claims priority to German Patent Application DE102015206985.0 filed Apr. 17, 2015 the entirety of which is incorporated by reference herein.
The invention relates to an engine cowling of an aircraft gas turbine according to features as disclosed herein.
In particular, the invention relates to an engine cowling (nacelle) of an aircraft gas turbine, comprising a stationary front area and a rear area that is displaceable in the axial direction. For one thing, the displacement of the rear area is effected for the purpose of opening an annular space between the front area and the rear area, so as to discharge the air flow from the bypass duct for thrust reversal. Furthermore, the rear area can be displaced by a shorter distance in order to modify the area nozzle of the bypass duct (cold nozzle) in its cross-section (VAN, variable area nozzle). Here, a small amount of air is discharged through the annular gap that is opened. This constellation is used to realize a maximal thrust of the aircraft gas turbine, for example. Additionally, this second position is also to be displaced in order to achieve the thrust reversal position.
It is known in the state of the art to guide and to mount the rear area of the engine cowling by means of rails. Such rail constructions, which can either be embodied in a telescope-like manner or in which guide rollers or the like glide along the rails, require elaborate constructions, are expensive to manufacture and lead to an increase in the weight of the entire aircraft gas turbine, since a support structure is required. Here, it is in particular necessary to reinforce rail systems so that they may resist lateral air flows or wind influences, for example in the event of a crosswind landing. Furthermore, these rail systems require an aerodynamic fairing (beaver tail fairing), which has a negative effect on performance.
In known constructions it has proven to be a disadvantage that, in addition to the above-mentioned increase in weight, additional friction is created. This additional friction makes stronger drive mechanisms necessary, which in turn results in more weight and greater space requirements. With a view to the space requirements, it has also proven to be disadvantageous that the accessibility of the components for purposes of maintenance is restricted.
The invention is based on the objective to create an engine cowling of the kind as it has been mentioned in the beginning, in which the disadvantages of the state of the art are avoided, while it is characterized by a simple structure as well as a simple and cost-effective manufacturing process, and at the same time facilitates safe mounting of the rear area of the engine cowling.
The objective is solved by a combination of features as disclosed herein, with the present disclosure showing further advantageous embodiments.
Thus, it is provided according to the invention that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal/VAN actuators that are arranged at an angle to each other. In thrust reversers, thrust reversal/VAN actuators according to the state of the art are always arranged in parallel to the engine axis.
Therefore, the solution principle according to the invention can substantially do without the rail constructions known from the state of the art. Instead, the actuators that are needed for the displacement of the rear area of the cowling are themselves used as load-bearing mounting elements. Thanks to this construction, it is in particular possible to sustain any occurring side loads, such as they may occur for example due to microbursts or during a crosswind landing, in a manner that is particularly operationally safe. In addition, a concentric mounting of the rear area of the engine cowling is guaranteed in all three operational positions (cruise flight, thrust reversal and modification of the cross-section of the area nozzle (VAN)). Here, it is provided in a particularly advantageous further development of the invention that the thrust reversal actuators form a framework structure. At that, they are preferably mounted in a hinged manner at their respective end areas, so that changes in length of the thrust reversal actuators contribute to the statics-based overall structure (Thruss principle).
The solution according to the invention ensures reliable and operationally safe mounting of the rear area in all three operational positions, namely in the cruise flight configuration in which the rear area has been displaced forward so as to connect to the front area, in a position for maximal thrust with a partial displacement of the rear area, as well as in a thrust reversal position with a complete backwards displacement. Here, rail systems with castors or the like can be substantially dispensed with. However, the upper rail systems can be retained as a safety mechanism. Without the upper rail systems, the solution according to the invention could also be used for thrust vectoring.
Thus, the overall result is a considerable weight reduction and a reduction of the aerodynamic losses of the outer flow. Further, particularly the access to the rear area of the aircraft gas turbine for maintenance purposes is considerably facilitated.
In the following, the invention is described based on an exemplary embodiment in connection with the drawing. Herein:
The gas turbine engine 10 according to
The medium-pressure compressor 13 and the high-pressure compressor 14 respectively comprise multiple stages, each of which has an array of fixedly attached, stationary guide blades 20 extending in the circumferential direction, which are generally referred to as stator blades and protrude radially inwards from the core engine cowling 21 through the compressors 13, 14 into a ring-shaped flow channel. The compressors further have an array of compressor rotor blades 22 that protrude radially outwards from a rotatable drum or disc 26 coupled with hubs 27 of the high-pressure turbine 16 or the medium-pressure turbine 17.
The turbine sections 16, 17, 18 have similar stages, comprising an array of fixedly attached guide blades 23 that protrude radially inward from the housing 21 through the turbines 16, 17, 18 into the ring-shaped flow channel, and a subsequent array of turbine blades 24 that protrude outward from a rotatable hub 27. During operation, the compressor drum or the compressor disc 26 and the blades 22 arranged thereon as well as the turbine rotor hub 27 and the turbine blades 24 arranged thereon rotate around the engine axis 1.
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