GB2530733A

GB2530733A - Gas Turbine Engine Mounting Arrangement

Info

Publication number: GB2530733A
Application number: GB1417201.9A
Authority: GB
Inventors: Glyn David Brain
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 2014-09-30
Filing date: 2014-09-30
Publication date: 2016-04-06
Also published as: GB201417201D0

Abstract

A mounting arrangement for attaching a gas turbine engine (10 see fig 1) to an aircraft is provided that has a mounting bracket 110 having fixing holes. The fixing holes are arranged in two sets either side of the centreline AA of the bracket 110. Each set of fixing holes has two outer fixing holes 112 and an intermediate fixing hole 114. The intermediate fixing hole 114 is further from the bracket centreline AA than the outer fixing holes 112 and is typically larger. Further intermediate holes and a complementary mounting block (140 see fig 5) may also be provided. The invention is at least aimed at providing for failsafe, reliable and weight minimised mounting of a gas turbine engine.

Description

GAS TURBINE ENGINE MOUNTING ARRANGEMENT

All modern aircraft are provided with power systems that need to be connected to an airframe. The connection between the power system and the airframe needs to be such that the power system can be carried by the airframe, and the thrust generated by the power system can be transferred to the airframe.

The thrust generated by modern gas turbine engines, such as turbofan engines, can be extremely high, for example up to and even in excess of 100000 lbs. Accordingly, the mounting arrangements that are required to attach the gas turbine engines to the airframes are necessarily strong enough to transfer such high loads, meaning that they contribute significantly to the weight of the gas turbine engine installation, and thus to the overall weight of the aircraft.

Furthermore, it is essential that the mounting arrangements operate reliably, and that they are provided with so called failsafe systems that ensure continued safe operation in the event that a part of the mounting arrangement fails or breaks. Such failsafe systems are essential, but further add to the weight of the gas turbine engine installation. Any additional weight is undesirably, for example because it leads to additional fuel burn, with the associated cost and environmental implications.

It is desirable to be able to mount a power plant (such as a gas turbine engine) to an aircraft in a reliable, failsafe, manner whilst minimizing the overall weight of the installation.

According to an aspect, there is provided a mounting bracket for mounting power plant (such as a gas turbine engine) to an aircraft. The bracket comprises fixing holes arranged either side of a bracket centreline. A first set of at least three fixing holes is provided on a first side of the bracket centreline. A second set of at least three fixing holes is provided on a second side of the bracket centreline. Each set of fixing holes comprises two outer fixing holes and an intermediate fixing hole. The two outer fixing holes are either side of the intermediate fixing hole with respect to a direction parallel to the bracket centreline. For each set of fixing holes, the distance between respective centrelines of each of the outer fixing holes and the bracket centreline is less than the distance between the centreline of the intermediate fixing hole and the bracket centreline.

It may be said that the distance between the centrelines of the intermediate fixing holes of the two sets of fixing holes is greater than the distance between the centrelines of two (for example any two or two corresponding) outer fixing holes from different sets of fixing holes.

Where reference is made to the distance between the centreline of a fixing hole and the bracket centreline, this may mean the perpendicular distance and/or the shortest distance.

According to an aspect, there is provided a mounting bracket for mounting a power plant (such as a gas turbine engine) to an aircraft. The bracket comprises fixing holes arranged either side of a bracket centreline. A first set of at least three fixing holes is provided on a first side of the bracket centreline. A second set of at least three fixing holes is provided on a second side of the bracket centreline. Each set of fixing holes comprises two outer fixing holes and an intermediate fixing hole. The two outer fixing holes are either side of the intermediate fixing hole with respect to a direction parallel to the bracket centreline. For each set of fixing holes, a centreline of the intermediate fixing hole and the bracket centreline are on opposite sides of an imaginary line joining the centrelines of the outer fixing holes.

The bracket centreline may not be parallel to the centrelines of the fixing holes. The bracket centreline may be substantially perpendicular to one or more (for example all) of the centrelines of the fixing holes. The bracket may be substantially planar, and the bracket centreline may be substantially parallel to the plane of the bracket. The bracket centreline may lie in a plane of symmetry of the bracket.

The mounting brackets described and/or claimed herein may provide a lightweight and/or reliable and/or failsafe arrangement for connecting a power plant to an aircraft. For example, providing an arrangement of outer fixing holes and intermediate fixing holes described and/or claimed herein means that if a fixing (such as a bolt) that passes through one of the fixing holes (for example an outer fixing hole) were to fail during operation, and/or if a part of the bracket were to fail, the intermediate fixing hole(s) would take a greater proportion of the increased load than the outer fixing holes. Accordingly, the intermediate fixing hole(s) of each set of fixing holes can be constructed and/or arranged to withstand the increased load in the event failure, whereas the remaining fixing holes (for example the outer fixing holes) may not be required to withstand such a large increased load, and can thus be constructed and/or arranged accordingly. This may allow the outer fixing holes (and/or the majority of the fixing holes) to be smaller and/or lighter and/or cheaper than would otherwise be required. For a typical engine set, this may save several kilograms of weight and/or several thousand dollars of cost.

The two outer fixing holes of each set of fixing holes may define the extent of that set of fixing holes along a direction parallel to the bracket centreline. The direction of a line between the centrelines of the outer fixing holes of a set of fixing holes may be parallel to (including substantially parallel to) the bracket centreline, although this need not be the case in all arrangements.

The fixing holes may have any suitable shape, for example to accommodate a desired fixing.

For example, the fixing holes may be circular in cross-section, for example to accommodate a threaded fixing such as a bolt or similar fixing.

The cross-sectional area of each of the outer fixing holes may be less than the cross-sectional area of the intermediate fixing hole of a set of fixing holes. For example, where the fixing holes have a circular cross-section, the diameter of the outer fixing holes may be less than the diameter of the intermediate fixing hole.

Each set of fixing holes may comprise any desired number of fixing holes, including the two outer fixing holes and at least one intermediate fixing hole. For example, a set of fixing holes may comprise no more than three fixing holes. Alternatively, a set of fixing holes may comprise more than three fixing holes, for example four, five, six, seven or more than seven fixing holes.

Where each set of fixing holes comprises more than three fixing holes, the set may comprise more than one intermediate fixing hole as defined and/or described herein.

Each set of fixing holes may comprise the same number of fixing holes. Thus, there may be the same number of fixing holes on each side of the bracket centreline.

The fixing holes may be symmetrically arranged about the centreline of the mounting bracket, for example in terms of their position and/or shape and/or size, such as their diameter where the holes have a circular cross-section.

For each set of fixing holes, the distance between respective centrelines of each of the outer fixing holes and the bracket centreline may be less than the distance between the centreline of any other fixing hole of that set and the bracket centreline.

The size and/or shape of the mounting bracket and/or the fixing holes may be determined according to its application, for example by the size and/or thrust of the gas turbine engine.

Purely by way of example, where the fixing holes have a circular cross-section, the diameter of each fixing hole may be in the range of from 1cm to 10cm, for example 1.5cm to 5cm, for example 2cm to 4cm. Purely by way of further example, the diameter of the outer fixing holes may be on the order of 2.7cm, and/or the diameter of the intermediate fixing hole(s) may be on the order of 3cm.

For each set of fixing holes, the area of the intermediate fixing hole may be in the range of from 2% and 100% bigger than the area of each of the outer fixing holes, for example 5% and 50% bigger, for example 10% and 40%, for example 15% and 30%, for example on the order of 20% bigger.

Where the fixing holes are circular in cross-section, for each set of fixing holes, the diameter of the intermediate fixing hole may be in the range of from 2% and 50% bigger than the diameter of each of the outer fixing holes, for example 5% and 25% bigger, for example 5% and 25% bigger, for example 7% and 20% bigger, for example 10% and 15% bigger, for example on the order of 11% bigger.

For each set of fixing holes, the distance between the bracket centreline and the centreline of the intermediate fixing hole may be in the range of from 0.5% and 10% greater than the distance between the bracket centreline and the respective centreline of the outer fixing holes, for example in the range of from 1% and 5%, for example on the order of 2.5%.

According to an aspect, there is provided a mounting arrangement for mounting a gas turbine engine to an aircraft. The mounting arrangement comprises a mounting bracket as described and/or claimed herein. The mounting arrangement comprises a mounting block having mounting block fixing holes that are complimentary to the fixing holes of the mounting bracket. In such a mounting arrangement, the mounting bracket comprises at least a part of a gas turbine engine mounting fixture that is connectable to the gas turbine engine (such a mounting fixture may, of course, be provided to any mounting bracket according to the present disclosure). In such an arrangement, the mounting block comprises at least a part of an aircraft mounting fixture that is connectable to an aircraft (for example to a pylon and/or a wing of an aircraft). In such an arrangement, the mounting bracket and mounting block are connected together using bolts, each of which passes through a fixing hole of the mounting bracket and a complimentary fixing hole of the mounting block.

According to an aspect, there is provided a gas turbine engine installation comprising a gas turbine engine and an aircraft. According to such an installation, the gas turbine engine is connected to the aircraft using the mounting bracket and/or mounting arrangement described and/or claimed herein.

According to an aspect, there is provided a method of mounting a gas turbine engine to an aircraft. The method comprises attaching a mounting arrangement including the mounting bracket as described and/or claimed herein to a gas turbine engine via the gas turbine engine mounting fixture of the mounting bracket. The method comprises also attaching the same mounting arrangement to an aircraft via the aircraft mounting fixture of the mounting block.

Any feature described and/or claimed herein may optionally be used in combination with any other compatible feature described and/or claimed herein.

Embodiments of the disclosure will now be described by way of non-limitative example with reference to the accompanying drawings in which: Figure 1 shows a cross-section through a gas turbine engine; Figure 2 shows a part of a gas turbine engine mounted to a pylon of an aircraft; Figure 3 shows a thrust strut and part of a mounting assembly used to attach a gas turbine engine to an aircraft; Figure 4 is a close-up view of the mounting assembly features shown in Figure 3; Figure 5 shows the mounting assembly shown in Figure 4 with additional features; Figure 6 shows a mounting bracket for use with a mounting assembly; Figure 7 shows an alternative mounting bracket for use with a mounting assembly; and Figure 8 shows a further alternative mounting bracket for use with a mounting assembly.

With reference to Figure 1, a ducted fan gas turbine engine generally indicated at 10 has a principal and rotational axis X-X. The engine 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, and intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. The engine also has a bypass duct 22 and a bypass exhaust nozzle 23.

The gas turbine engine 10 works in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.

The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines 16, 17, 18 respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.

Each of the high, intermediate and low-pressure turbines 16, 17, 18 and the intermediate and high-pressure compressors 13, 14 comprises at least one stage comprising a set of rotor blades and a set of stator vanes. In use, the rotor blades rotate around the engine axis X-X, whilst the stator vanes are stationary within the engine.

It will be appreciated that the gas turbine engine 10 if Figure 1 is shown by way of example only, and the present disclosure may be applied to any other type of gas turbine engine, for example with any arrangement of turbines, compressors, shafts and casings.

Figure 1 also shows a pylon 300 to which the gas turbine engine 10 is mounted via a front mounting arrangement 500, and a rear mounting arrangement 100 to form a gas turbine engine installation. The gas turbine engine installation also comprises a thrust strut 200, through which the motive force generated by the engine is transmitted to the pylon 300. The pylon 300 may be a part of an aircraft (for example attached to the wing of an aircraft), and thus the gas turbine engine installation may be part of an aircraft. Further details of the gas turbine engine installation are discussed below in relation to Figures 2 to 8.

Figure 2 shows a perspective view of the schematic cross-section shown in Figure 1, with only a part of the engine 10 being shown in Figure 2. In this exemplary arrangement, the front and rear mounting arrangements 100, 500 are connected to casings of the gas turbine engine 10. In particular, the front mounting 500 is connected to a fan casing 50, and the rear mounting 100 is connected to a core casing 40. The thrust strut 200 is connected between the core casing 40 and the rear mounting 100, although it will be appreciated that other arrangements are also possible.

Figures 3 and 4 show a part of the rear mounting arrangement 100 and the thrust strut 200 in greater detail, with Figure 4 being a close-up of the mounting arrangement 100, and will be discussed together.

The mounting arrangement 100 comprises a mounting bracket 110. The mounting bracket is connectable to the gas turbine engine structure 10 (for example to the casing 40 shown in Figure 2) via a gas turbine engine mounting fixture 119, which may comprise, for example, a hole through the mounting bracket 110 that is connected to a connecting link 190 using a pin 194. The connecting link 190 may then be connected to the casing 40 of the gas turbine engine 10 (for example to lugs 42 on the casing, as shown in Figure 2) via a further pin 192. A mounting arrangement 100 may comprise more than one such fixture 119 and associated connecting features 190, 192, 194 for connecting the mounting bracket 110 to the gas turbine engine 10.

The mounting bracket 110 is connected to the aircraft structure (such as a pylon) 300 via a mounting block 140. The mounting block 140 is not shown in Figures 3 and 4 so as to assist the understanding of the mounting bracket arrangement 110, but the mounting bracket 110 is shown assembled to the mounting block 140 in Figure 5. The mounting block 140 comprises an aircraft mounting fixture, a part of which is shown as feature 149 in FigureS, that is connectable to an aircraft structure, such as a pylon 300. Purely by way of example, the aircraft mounting fixture may comprise, for example, holes through which securing elements such as bolts may be inserted.

A number of securing elements 122, 124, 126 (collectively referred to as securing elements 120) are provided. Such securing elements 120 may be, for example, bolts. The securing elements 120 pass through holes in both the mounting bracket 110 and the mounting block in order to secure the two mounting features together, and thus secure the engine 10 to the pylon 300.

The mounting bracket 110 must be reliably connected to the mounting block 140 in a manner that is fail-safe, such that in the event of a failure of a part of the mounting arrangement 100 safe operation is assured. To this end, the securing elements 120 are designed to have redundancy, meaning that in the event of failure of one (or optionally even more than one) securing element 120, the mounting bracket 110 and the mounting block 140 remain connected together. However, this redundancy necessarily adds weight to the structure. The arrangements of fixing holes and/or securing elements 120 described and/or claimed herein may allow the required levels of redundancy at minimal extra weight.

Figure 6 shows a schematic of an example of a mounting bracket 110. The mounting bracket 100 comprises fixing holes 112, 114. The fixing holes 112, 114 receive respective securing elements 120 (such as bolts) in order to attach the mounting bracket 110 to the aircraft structure 300. In the illustrated exemplary arrangements, the mounting bracket 110 is attached to the aircraft structure 300 via the mounting block 140, which accordingly may have a similar (for example identical) arrangement of fixing holes to those fixing holes 112, 114 shown with respect to the mounting bracket 110. However, it will be appreciated that the mounting bracket may be connected to the aircraft structure in other arrangements, for example by direct connection to fixing holes in the aircraft structure.

The fixing holes 112, 114 in the mounting bracket 110 are arranged in two sets of fixing holes 115, 116 either side of a centreline A-A of the mounting bracket 110. Each set of fixing holes 115, 116 has two outer fixing holes 112. In the examples shown in Figure 6 to 8, the outer fixing holes 112 may be said to be the outermost holes at either end of the set of fixing holes 115, 116, for example with respect to the direction of the bracket centreline A-A.

Thus, the outer fixing holes 112 may be said to define the extent of the holes in a set 115, 116 in the direction of the bracket centreline A-A. The outer fixing holes 112 (that is, the centrelines thereof, which are in the direction into the page in Figures 6 to 8) are at a distance q from the bracket centreline A-A. The distance q may be said to be the closest distance and/or the perpendicular distance between the centrelines of the bracket 110 and the holes 112.

Each set of fixing holes 115, 116 also comprises an intermediate fixing hole 114. The intermediate fixing hole 114 is in between the two outer fixing holes 112 in the direction defined by the bracket centreline A-A. The intermediate fixing hole 114 (that is, the centreline thereof, which is in the direction into the page in Figures 6 to 8) is at a distance r from the bracket centreline A-A. The distance r may be said to be the closest distance and/or the perpendicular distance between the centrelines of the bracket 110 and the holes 114. The distance r is greater than the distance q defined above in relation to the outer fixing holes 112, as shown by the dimension p. Accordingly, the distance q between respective centrelines of each of the outer fixing holes 112 and the bracket centreline A-A is less than the distance r between the centreline of the intermediate fixing hole 114 and the bracket centreline A-A.

The arrangement of Figure 6 is an example of an arrangement in which the securing element 124 passing through the intermediate fixing hole 114 would take a greater load (for example a greater proportion of the excess load) than the securing elements 122, 126 passing through the outer fixing holes 112 in the event of a failure, for example in the event that one of the fixing holes 112, 114 and/or the securing elements 120 failed. Accordingly, the securing elements 122, 126 passing through the outer fixing holes 112 can be designed to carry a lower load than the securing element 124 passing through the intermediate fixing hole 114. The securing elements 122, 126 passing through the outer fixing holes 112 can be cheaper and/or smaller and/or lighter than the securing element 124 passing through the intermediate fixing hole 114.

In the example of Figure 6, the area of the intermediate fixing hole 114 (and thus the cross-section of the securing element 124 passing therethrough) is greater than the area of each of the outer fixing holes 112 (and thus the cross-sectional area of each of the securing elements 122, 126 passing therethrough). In the Figure 6 arrangement, the fixing holes 112, 114 have a circular cross-section, so the diameter I of the outer fixing holes 112 is less than the diameter m of the intermediate fixing hole 114.

Examples of the actual and relative dimensions of the fixing holes 112, 114 and the distances of those holes 112, 114 from the bracket centreline A-A are provided elsewhere herein.

Various different arrangements of fixing holes 112, 114 (and/or of the respective securing elements 120) may be provided. Figures 7 and 8 show two further possible arrangements of fixing holes, purely by way of non-limitative example.

In the Figure 7 arrangement, the outer fixing holes 112 and the intermediate fixing hole 114 of each set of holes 115, 116 may be arranged substantially as described above in relation to Figure 6. However, each set of fixing holes 115, 116 in the Figure 7 arrangement has two additional fixing holes 113. The additional fixing holes 113 have an area smaller than that of the intermediate fixing hole 114. The additional fixing holes 113 are located closer to the bracket centreline A-A than is the intermediate fixing hole 114. The additional fixing holes 113 may, for example, be substantially the same as the outer fixing holes 112, for example in terms of distance from the bracket centreline A-A and/or area and/or cross-sectional shape. Providing such additional fixing holes 113 may be appropriate for some applications, for example depending on the loading requirements.

In the Figure 8 arrangement, the outer fixing holes 112 and the intermediate fixing hole 114 of each set of holes 115, 116 may be arranged substantially as described above in relation to Figure 6. However, each set of fixing holes 115, 116 in the Figure 8 arrangement has two additional fixing holes 118. In the Figure 8 arrangement, the additional fixing holes 118 may, for example, be substantially the same as the intermediate fixing hole 114, for example in terms of distance from the bracket centreline A-A and/or area and/or cross-sectional shape.

Accordingly, the additional fixing holes 118 may also be referred to as intermediate fixing holes 114. Thus, a mounting bracket 110 may be provided with a set of fixing holes 115, 116 that comprises two outer fixing holes 112, and more than one intermediate fixing hole 114, 118. This arrangement may be beneficial, for example depending on the loading requirements.

Where reference is made herein to a gas turbine engine, it will be appreciated that this term may include may be any type of gas turbine engine, including, but not limited to, a turbofan (bypass) gas turbine engine, turbojet, turboprop, ramjet, scramjet or open rotor gas turbine engine, and for any application, for example aircraft, industrial, and marine application.

Furthermore, it will be appreciated that many different arrangements in addition to those described herein may fall within the scope of the attached claims. Purely by way of non-limitative example, different arrangements of fixing holes in terms of, for example, number, positioning, relative positioning, shape and/or size may fall within the scope of the claims.

Claims

CLAIMSA mounting bracket (110) for mounting a gas turbine engine (10) to an aircraft (300), the bracket comprising fixing holes (112, 114) arranged either side of a bracket centreline (A-A), wherein: a first set (115) of at least three fixing holes is provided on a first side of the bracket centreline and a second set (116) of at least three fixing holes is provided on a second side of the bracket centreline; each set of fixing holes comprises two outer fixing holes (112) and an intermediate fixing hole (114), the two outer fixing holes being either side of the intermediate fixing hole with respect to a direction parallel to the bracket centreline; and for each set of fixing holes, the distance (q) between respective centrelines of each of the outer fixing holes and the bracket centreline is less than the distance (r) between the centreline of the intermediate fixing hole and the bracket centreline.
2. A mounting bracket according to claim 1, wherein the two outer fixing holes of each set of fixing holes define the extent of that set of fixing holes along a direction parallel to the bracket centreline.
3. A mounting bracket according to claim 1 or claim 2, wherein the fixing holes are circular in cross-section, and the diameter (I) of the outer fixing holes is less than the diameter (m) of the intermediate fixing hole.
4. A mounting bracket according to any one of the preceding claims, wherein each set of fixing holes comprises no more than three fixing holes.
5. A mounting bracket according to any one of claims 1 to 3, wherein each set of fixing holes comprises more than three fixing holes.
6. A mounting bracket according to claim 5, wherein each set of fixing holes comprises more than one intermediate fixing hole (114, 118) having a centreline that is further from the bracket centreline than the distance between respective centrelines of each of the outer fixing holes of that set of fixing holes and the bracket centreline.
7. A mounting bracket according to any one of the preceding claims, wherein the fixing holes are symmetrically arranged about the centreline of the mounting bracket.
8. A mounting bracket according to any one of the preceding claims, wherein for each set of fixing holes, the distance between respective centrelines of each of the outer fixing holes and the bracket centreline is less than the distance between the centreline of any other fixing hole of that set and the bracket centreline.
9. A mounting bracket according to any one of the preceding claims, wherein the fixing holes have a circular cross-section, and the diameter of each fixing hole is in the range of from 2cm to 4cm.
10. A mounting bracket according to any one of the preceding claims, wherein, for each set of fixing holes, the area of the intermediate fixing hole is in the range of from 5% and 50% bigger than the area of each of the outer fixing holes.
11. A mounting bracket according to any one of the preceding claims, wherein, for each set of fixing holes, the distance between the bracket centreline and the centreline of the intermediate fixing hole is in the range of from 0.5% and 10% greater than the distance between the bracket centreline and the respective centreline of the outer fixing holes.
12. A mounting bracket (110) for mounting a gas turbine engine (10) to an aircraft (300), the bracket comprising fixing holes (112, 114) arranged either side of a bracket centreline (A-A), wherein: a first set (115) of at least three fixing holes is provided on a first side of the bracket centreline and a second set (116) of at least three fixing holes is provided on a second side of the bracket centreline; each set of fixing holes comprises two outer fixing holes (112) and an intermediate fixing hole (114), the two outer fixing holes being either side of the intermediate fixing hole with respect to a direction parallel to the bracket centreline; and for each set of fixing holes, a centreline of the intermediate fixing hole and the bracket centreline are on opposite sides of an imaginary line joining the centrelines of the outer fixing holes.
13. A mounting arrangement (100) for mounting a gas turbine engine (10) to an aircraft (300) comprising: a mounting bracket (110) according to any one of the preceding claims; and a mounting block (140) having mounting block fixing holes that are complimentary to the fixing holes of the mounting bracket, wherein the mounting bracket comprises at least a part of a gas turbine engine mounting fixture (119) that is connectable to the gas turbine engine; the mounting block comprises at least a part of an aircraft mounting fixture (149) that is connectable to an aircraft; and the mounting bracket and mounting block are connected together using bolts (120), each of which passes through a fixing hole of the mounting bracket and a complimentary fixing hole of the mounting block.
14. A gas turbine engine installation comprising: a gas turbine engine (10); and an aircraft (300), wherein the gas turbine engine is connected to the aircraft using the mounting bracket (110) of any one of claims ito 12 and/or the mounting arrangement (100) of claim 13.
15. A method of mounting a gas turbine engine (10) to an aircraft (300) comprising: attaching the mounting arrangement of claim 13 to the gas turbine engine via the gas turbine engine mounting fixture of the mounting bracket; and also attaching the same mounting arrangement of claim 13 to the aircraft via the aircraft mounting fixture of the mounting block.