Gas turbine engine controller

Abstract

A gas turbine engine is provided, comprising: a turbine; a fan section having a fan rotatable by the turbine; a nacelle surrounding the fan; and an engine controller located within the nacelle. The nacelle defines an inner surface radius (r) of the engine controller in a radial direction, wherein the engine controller defines a radial height (Δr), a total volume (V), and a normalized radius (r′) in the radial direction. The normalized radius (r′) is the ratio of the inner surface radius (r) to the cube root of the total volume (V), wherein these parameters are related by the following equation: where the normalized radius (r′) is between 1.25 and 8 and K equals 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K equals 65%.

Description

Technical Field

[0001] This disclosure relates to an engine controller for a gas turbine engine, and a gas turbine engine having the engine controller. Background Technology

[0002] Gas turbine engines typically consist of a turbine and a rotor assembly. Gas turbine engines, such as turbofan engines, are used for aircraft propulsion. In the case of a turbofan engine, the rotor assembly can be configured as a fan assembly. A nacelle can be arranged around the fan assembly to increase the propulsive efficiency of the turbofan engine. In at least some configurations, the controller for the engine, such as a full-authority digital engine control controller, can be located within the nacelle. Improving turbofan engines to increase their propulsive efficiency is welcome in the art. Attached Figure Description

[0003] The specification sets forth a complete and practical disclosure for those skilled in the art, including its best mode, which is referenced in the accompanying drawings, wherein:

[0004] Figure 1 This is a cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.

[0005] Figure 2 This is viewed along the axial direction of the gas turbine engine. Figure 1 A schematic diagram of the nacelle and a portion of the engine controller of an exemplary gas turbine engine.

[0006] Figure 3 yes Figure 2 A close-up schematic diagram of the nacelle and engine controller of an exemplary gas turbine engine.

[0007] Figure 4 This is a schematic diagram of a portion of the nacelle and engine controller of a gas turbine engine according to another exemplary embodiment of the present disclosure.

[0008] Figure 5 This is a schematic diagram of a portion of the nacelle and engine controller of a gas turbine engine according to yet another exemplary embodiment of the present disclosure.

[0009] Figure 6A and Figure 6B It is a table that includes values ​​corresponding to several gas turbine engines according to exemplary aspects of this disclosure.

[0010] Figure 7 It is a graph of a gas turbine engine according to one or more exemplary embodiments of the present disclosure. Detailed Implementation

[0011] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Detailed description uses numerals and letter designations to refer to features in the drawings. Similar or identical reference numerals in the drawings and description have been used to refer to similar or identical portions of the present disclosure.

[0012] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or beneficial to other implementations. Furthermore, unless specifically stated otherwise, all embodiments described herein should be considered exemplary.

[0013] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0014] The term "turbine" refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines, which together produce torque output.

[0015] The term "gas turbine engine" refers to an engine that has a turbine as its power source, either entirely or partially. Exemplary gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid versions of one or more of these engines.

[0016] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term combustion section may refer to a section including one or more of a knock combustion assembly, a rotary detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assembly. In some exemplary embodiments, the combustion section may include an annular burner, a can burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0017] When used with compressors, turbines, shafts, or spools, unless otherwise specified, the terms “low” and “high,” or their respective degrees of comparison (e.g., moreover, where applicable), each refer to a relative speed within the engine. For example, “low-speed turbine” or “low-turbine” defines a component configured to operate at a speed lower than that of the engine’s “high-speed turbine” or “high-turbine,” such as the maximum permissible speed.

[0018] Throughout this specification and claims, scope limitations are combined and interchanged, and such scopes are identified and include all subscopes contained therein, unless the context or language otherwise indicates. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0019] Unless otherwise stated herein, the terms “connection”, “fixation”, etc., refer to both direct connection, fixation or attachment and indirect connection, fixation or attachment through one or more intermediate components or features.

[0020] The goal in designing turbofan engines is typically to maximize their propulsive efficiency. Generally, turbofan engines include relatively large fans to provide the desired amount of thrust without overloading the fan blades (i.e., without increasing the disk load on the fan blades beyond a certain threshold), and thus maintaining the desired overall propulsive efficiency. Turbofan engine design practice can further strive to provide large fans, or more precisely, large-diameter fans, to allow the fan to provide as much of the reasonably possible total thrust as possible. However, including such large fans can lead to problems such as encapsulating the turbofan engine within the aircraft, and relatively heavy turbofan engines (because the nacelle size necessarily increases with the fan diameter). Efforts can be made to reduce the nacelle size of turbofan engines with relatively large fans by reducing the nacelle's radial height. However, it is worth noting that turbofan engines may include engine controllers mounted within the nacelle. The radial height of the engine controllers can define the minimum radial height of the nacelle, which, once mounted on the aircraft, can in turn significantly impact the nacelle weight, the amount of air resistance on the turbofan engine, and the amount of clearance between the turbofan engine and the ground.

[0021] The inventors of this disclosure have discovered that in order to reduce the radial height of the engine compartment, the height of the engine controller must also be reduced. However, as the height of the engine controller decreases, its weight increases. The further the shape of the engine controller deviates from, for example, a cube shape, the more housing material is required to provide a given internal volume for circuit boards, connectors, etc. Therefore, there is a trade-off between wanting to reduce the radial height and avoiding excessive weight increase.

[0022] The inventors approached the design of a turbofan engine with given fan characteristics (e.g., fan diameter) and corresponding nacelle weight and height designed for various engine controllers; examined the propulsion efficiency of the designed turbofan engine; examined structural issues related to the weight of the engine controller and nacelle; redesigned turbofan engines with different fan characteristics (e.g., fan diameter) and corresponding nacelle weight and height designed for various engine controllers; re-examined the propulsion efficiency of the designed turbofan engine; re-examined structural issues related to the weight of the engine controller and nacelle; and so on. During the design of several different types of turbofan engines, the following references were included. Figures 1 to 5The gas turbine engine described. In the process of studying / evaluating various key fan characteristics of the feasible options considered to best meet mission requirements and the corresponding nacelle weight and altitude for various engine controller designs, it was found that the ratio of the radial range of the engine controller to the fan diameter ( ) and normalized engine controller radius (inner surface radius of the engine compartment ( ) and the total volume of the engine controller ( The ratio of the cube roots of ( ); There is a certain relationship between them.

[0023] The resulting relationship can be considered as an indicator of a turbofan engine's ability to maintain or even improve its desired propulsion efficiency by incorporating the desired fan diameter while also taking into account the packaging and weight of the engine controller and nacelle.

[0024] Referring now to the accompanying drawings, where the same numerals throughout the drawings denote the same elements. Figure 1 A schematic cross-sectional view of an engine according to an exemplary embodiment of the present disclosure is provided.

[0025] In the illustrated embodiment, the engine is configured as a high-bypass turbofan engine 100. As... Figure 1 As shown, the turbofan engine 100 defines an axial direction A (extending parallel to the centerline axis 101 provided for reference), a radial direction R, and a circumferential direction (extending about the axial direction A). Figure 1 (Not depicted in the text). Typically, the turbofan engine 100 includes a fan section 102 and a turbine 104 disposed downstream of the fan section 102.

[0026] The exemplary turbine 104 shown generally includes a generally tubular housing 106 defining an annular inlet 108. The housing 106 surrounds, in a series flow relationship, a compressor section including a turbocharger or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including a high-pressure (HP) turbine 116 and a low-pressure (LP) turbine 118; and an exhaust nozzle section 120. The compressor section, combustion section 114, and turbine section together at least partially define a core airflow path 121 extending from the annular inlet 108 to the exhaust nozzle section 120. The turbofan engine also includes one or more drive shafts. More specifically, the turbofan engine 100 includes a high-pressure (HP) shaft or shaft 122 drivingly connecting the HP turbine 116 to the HP compressor 112, and a low-pressure (LP) shaft or spool 124 drivingly connecting the LP turbine 118 to the LP compressor 110.

[0027] In the illustrated embodiment, fan section 102 includes a fan 126 having a plurality of fan blades 128 spaced apart and coupled to disk 130. The plurality of fan blades 128 and disk 130 together can be rotated about a centerline axis 101 via LP shaft 124. Disk 130 is covered by a rotatable front hub 132 having an aerodynamic profile to facilitate airflow through the plurality of fan blades 128. Furthermore, an annular fan housing or nacelle 134 is provided, circumferentially surrounding at least a portion of fan 126 and / or turbine 104. Nacelle 134 is supported relative to turbine 104 by a plurality of circumferentially spaced outlet guide blades 136. A downstream section 138 of nacelle 134 extends above and outside turbine 104 to define a bypass airflow passage 140 therebetween.

[0028] In this way, it will be understood that the turbofan engine 100 typically includes a first flow (e.g., a core airflow path 121) and a second flow extending parallel to the first flow (e.g., a bypass airflow passage 140). In some exemplary embodiments, the turbofan engine 100 may also define a third flow, for example, extending from the LP compressor 110 to the bypass airflow passage 140 or to the environment. With such a configuration, the LP compressor 110 typically includes a first compressor stage and a downstream compressor stage configured as a ducted fan. The inlet of the third flow may be located between the first compressor stage and the downstream compressor stage.

[0029] However, it should be understood that Figure 1 The exemplary turbofan engine 100 depicted is provided by way of example only. In other exemplary embodiments, any other suitable gas turbine engine may be used in conjunction with aspects of this disclosure. For example, in other embodiments, the turbofan engine may be any other suitable gas turbine engine, such as a turboshaft engine, a turboprop engine, a turbojet engine, etc. In this way, it will be further understood that in other embodiments, the gas turbine engine may have any other suitable configuration, such as any other suitable number or arrangement of shafts, compressors, turbines, fans, etc. Furthermore, although Figure 1The exemplary gas turbine engine depicted herein is schematically shown as a direct-drive, fixed-pitch turbofan engine; however, in other embodiments, the gas turbine engine of this disclosure may be a geared gas turbine engine (i.e., a gearbox including a fan 126 and a shaft (e.g., LP shaft 124) driving the fan), a variable-pitch gas turbine engine (i.e., a fan 126 including a plurality of fan blades 128 rotatable about their respective pitch axes), etc. Furthermore, while the exemplary turbofan engine 100 includes a ducted fan 126, in other exemplary aspects, the turbofan engine 100 may include a ductless fan 126 (or an open rotor fan) without a nacelle 134. Additionally, although not described herein, in other embodiments, the gas turbine engine may be any other suitable type of gas turbine engine, such as a marine gas turbine engine.

[0030] Still refer to Figure 1 It should be understood that the exemplary turbofan engine 100 also includes an engine controller 150. More specifically, for the described embodiment, the engine controller 150 is located within a nacelle 134 (e.g., within the housing of the nacelle 134), and more specifically, is mounted within the nacelle 134 at a location above the plurality of fan blades 128 of the fan 126 (e.g., aligned with the plurality of fan blades 128 of the fan 126 in an axial direction A). In particular, the nacelle 134 includes an inner wall 152 defining an inner surface 154 located outside the plurality of fan blades 128 of the fan 126, to which the engine controller 150 is mounted or otherwise positioned adjacent to the inner wall 152.

[0031] In at least some exemplary embodiments, engine controller 150 may be a full authority digital engine control (“FADEC”) controller. However, in other embodiments, other suitable engine controllers may be provided. For example, in other embodiments, engine controller 150 may include a health monitoring unit and other electronic systems.

[0032] It should be understood that although the engine controller 150 is described as being mounted within the nacelle 134 at a location above the plurality of fan blades 128 of the fan 126, in at least some exemplary embodiments, the engine controller 150 may be positioned in the axial direction A in front of the plurality of fan blades 128 of the fan 126, or it may be positioned in the axial direction A behind the plurality of fan blades 128 of the fan 126. Typically, the engine controller 150 is mounted within the nacelle 134 at a location with the maximum radial range.

[0033] from Figure 1 In the illustrated embodiment, it can also be understood that the nacelle 134 defines the inner surface radius of the engine controller 150 in the radial direction R. Inner surface radius () The radius R refers to the distance along the radial direction R from the centerline axis 101 to the inner surface 154 of the engine compartment, relative to the inner wall 152 where the engine controller 150 is installed. More specifically, the inner surface radius ( The length R along the radial direction from the centerline axis 101 to the inner surface 154 of the nacelle, at the location of the plurality of fan blades 128 along the centerline axis 101, and more specifically, at the location where the leading edge of the plurality of fan blades 128 along the centerline axis 101 meets the corresponding outer tip of the plurality of fan blades 128.

[0034] Furthermore, the engine controller 150 and the nacelle interior surface 154 define the radial height along the radial direction R. Radial height ( Radial height (R) refers to the distance along the radial direction R from the inner surface 154 to the outermost surface of the engine controller 150 along the radial direction R. The radial height is measured in a plane perpendicular to the centerline axis 101 (for the illustrated embodiment, the plane defined by the radial direction R; "radial plane"). In the illustrated embodiment, where the engine controller 150 is positioned above the plurality of fan blades 128, the radial height ( This refers to the distance R along the radial direction from the inner surface 154 to the outermost surface of the engine controller 150 along the radial direction R at the location of the plurality of fan blades 128 along the centerline axis 101. In this way, in Figure 1 In the embodiment, the inner surface radius ( ) and radial height ( All of them are confined to the same radial plane.

[0035] However, in other embodiments, for example, when the engine controller 150 is positioned in front of or behind the plurality of fan blades 128, the radial height ( Alternatively, it can be defined at different locations along the centerline axis 101—the location of the outermost surface of the engine controller 150 in the radial direction R.

[0036] In the illustrated embodiment, the inner surface radius ( ) and radial height ( All are confined to the same radial plane, and the radial height ( ) and inner surface radius ( The sum of ) determines the position of the engine controller 150 relative to the engine centerline axis 101 at its radial outermost position, and the inner surface radius ( Twice the length of the radial height () ) (i.e., 2× + () is the distance from the outermost radial position of the engine controller 150 to the opposite wall 152.

[0037] More specifically, now also refer to Figure 2 A schematic diagram of a portion of the nacelle 134 and engine controller 150, viewed along the axial direction A of the turbofan engine 100, is provided. It should be understood that the radial height ( More specifically, it refers to the distance along the radial direction R from the inner surface 154 opposite to the inner wall 152 of the engine controller 150 to the outermost point of the outermost surface of the engine controller 150 along the radial direction R. Although Figure 2 The inner wall 152 is schematically depicted as a single line, but it should be understood that the radial height ( The thickness of the inner wall 152 was included in its measurement.

[0038] In addition, see also Figure 2 It should be understood that the engine controller 150 defines the length L along the axial direction A (see...). Figure 1 Width W (see) Figure 2 ), height H (see Figure 2 ), outer surface area SA (not shown), and total volume V. For a box-shaped engine controller 150, for example... Figure 1 and Figure 2 The outer surface area SA of the controller described herein refers to the surface area of ​​the top surface 156 of the engine controller 150, which can be the product of the length L and the width W of the engine controller 150. Further, for a box-shaped engine controller 150, the total volume V refers to the product of the length L, the width W, and the height H of the engine controller 150.

[0039] As explained in more detail elsewhere in this document, the engine controller 150 is typically configured as a conformal engine controller, which is configured to have a relatively small radial footprint, thereby enabling, for example, a larger diameter fan 126, a higher bypass ratio (i.e., the ratio of airflow through the bypass airflow passage 140 to airflow through the annular inlet 108; see Figure 1 This would result in higher propulsion efficiency, among other things. To achieve this, one might simply conclude that the housing of the engine controller 150 should be designed with a larger outer surface area SA. However, a simple increase in surface area (or a reduction in the profile in the radial plane) could lead to an unacceptable increase in the weight of the engine controller 150.

[0040] Now for reference Figure 3The diagram provides a close-up schematic of an exemplary engine controller 150 and a cabin 134. It should be understood that the exemplary engine controller 150 typically includes an outer housing 160 defining a casing 162, one or more circuit boards 164 positioned within the casing 162, and an electrical connector 166 mounted to the outer housing 160 for connecting the one or more circuit boards 164 to a turbofan engine 100 and / or various aspects of an aircraft containing the turbofan engine 100. Notably, the circuit board 164 may include one or more components 168, such as one or more memory components, resistors, transistors, capacitors, inductors, transformers, diodes, sensors, etc.

[0041] In the illustrated embodiment, electrical connector 166 is positioned at one end of engine controller 150 in the circumferential direction C. It should be understood that electrical connector 166 defines a height 170. The height 170 of electrical connector 166 can be at least 50%, for example at least 70%, for example at least 80%, for example at least 90%, for example up to 120%, of the height H of engine controller 150. In this way, it will be understood that the height 170 of electrical connector 166 can affect the height H of engine controller 150, and thus affect the radial height of engine compartment 134.

[0042] It should be understood that although the electrical connector 166 of the engine controller 150 is positioned at one end of the engine controller 150 in the circumferential direction C, in other embodiments, the electrical connector 166 may alternatively be positioned at one end of the engine controller 150 in the axial direction A. Alternatively, the engine controller 150 may still include multiple electrical connectors 166 at different locations.

[0043] It should be understood that, although for Figure 2 and Figure 3 In one embodiment, the engine controller 150 is designed to have a relative box shape (e.g., a rectangle / shared side perpendicular to all adjacent sides), but in other embodiments of this disclosure, the engine controller 150 may have any other suitable design capable of achieving the desired reduced radial footprint.

[0044] For example, now refer to Figure 4 A schematic diagram of a portion of a nacelle 134 and an engine controller 150 according to another exemplary embodiment of the present disclosure, viewed along the axial direction A of the turbofan engine 100. The exemplary nacelle 134 and engine controller 150 can generally be described with reference to the foregoing. Figures 1 to 3 The exemplary cabin 134 and engine controller 150 described are configured in a similar manner.

[0045] However, for the depicted embodiment, the engine controller 150 typically defines a curved profile. More specifically, it should be understood that the turbofan engine 100 typically defines a reference plane perpendicular to the axial direction A (i.e., Figure 4 The plane seen in the image). The housing of the engine controller 150 ( Figure 4 Unmarked; see also Figure 3 The outer housing 160 of the engine controller 150 defines a curved profile in a reference plane. More specifically, the housing of the engine controller 150 defines an inner curved profile 172 and an outer curved profile 174. The inner curved profile 172 may define a radius of curvature in the reference plane, which does not exceed the inner surface radius of the cabin 134. 50% of the inner curved profile 172. For example, in some exemplary embodiments, the inner curved profile 172 may define a radius of curvature in a reference plane, which is 50% of the inner surface radius. Within 25% of, for example, within the inner surface radius ( Within 10% of the radius of curvature of the inner curved profile 172. Furthermore, in at least some exemplary aspects, the outer curved profile 174 may define a radius of curvature in a reference plane that is within 20% of the radius of curvature of the inner curved profile 172.

[0046] It is worth noting that, such as Figure 4 As shown by the dashed lines, the exemplary engine controller 150 also includes one or more circuit boards 164. For the depicted embodiment, the one or more circuit boards 164 define a curved profile in a reference plane perpendicular to the axial direction A. This allows one or more circuit boards 164 of desired dimensions to be more compactly fitted within the engine controller 150 having the curved profile. The curved profile of the circuit board 164 may have a radius of curvature within the range described above for the inner curved profile 172 and the outer curved profile 174.

[0047] Furthermore, it should be understood that in other exemplary embodiments, the engine controller 150 according to the exemplary embodiments of this disclosure may have other suitable configurations. For example, now referring to... Figure 5 A schematic diagram of a portion of a nacelle 134 and an engine controller 150 according to another exemplary embodiment of the present disclosure, viewed along the axial direction A of the turbofan engine 100. The exemplary nacelle 134 and engine controller 150 are generally comparable to those referenced above. Figures 1 to 4 The exemplary cabin 134 and engine controller 150 described are configured in a similar manner.

[0048] However, in the described embodiment, the engine controller 150 is not configured as a single discrete box, but rather includes a plurality of discrete boxes spaced apart along the circumferential direction C of the turbofan engine 100. Specifically, in the described embodiment, the engine controller 150 includes two discrete boxes spaced apart along the circumferential direction C. However, in other exemplary embodiments, the engine controller 150 may include any other suitable number of discrete boxes (e.g., between 2 and 10). The plurality of discrete boxes may be along the circumferential direction C, along the axial direction A (see...). Figure 1 (or the two are separated.)

[0049] In this exemplary embodiment, it should be understood that the total volume V of the engine controller 150 refers to the sum of the total volumes V of each of the plurality of discrete boxes of the engine controller 150. Similarly, the outer surface area SA of the engine controller 150 refers to the sum of the outer surface areas SA of the top surface 156 of each of the plurality of discrete boxes.

[0050] In other exemplary embodiments, the engine controller 150 may have other configurations. For example, in other exemplary embodiments, the engine controller 150 may have a faceted profile. More specifically, the engine controller 150 may include an effective curved profile (similar to...). Figure 5 (An embodiment), but with multiple flat surfaces along the circumferential direction C, so the internal circuit board 164 can be flat. This will approximate Figure 5 The design features a curved form factor, but still utilizes a flat circuit board (164). Similar to... Figure 5 Compared to the multi-box design of other embodiments, this configuration can also save on wiring weight. For example, in some exemplary embodiments, the engine controller 150 may include two to 20 flat surfaces (which may appear as two to 20 flat box-shaped controller boxes welded or otherwise connected together to have a common internal volume) arranged in the circumferential direction C.

[0051] As mentioned earlier, during the design process of turbofan engines—that is, evaluating different turbofan engines, each with varying fan characteristics (e.g., fan diameter) that lead to different effects on nacelle weight and height, and related modifications to the engine controller weight and packaging—the inventors unexpectedly discovered that the ratio of the engine controller's radial range to the fan diameter ( ) and normalized engine controller radius (inner surface radius ( ) and the total volume of the engine controller ( There is a relationship between the ratio of the cube roots of the controller height and the normalized controller radius. The resulting relationship between the relative controller height and the normalized controller radius can be considered as an indicator of the turbofan engine's ability to maintain or even improve the desired propulsion efficiency by incorporating the desired fan diameter while also considering the packaging and weight of the engine controller and nacelle.

[0052] As will be understood, it is generally desirable to increase the diameter of the fan in a ducted turbofan engine to increase the overall propulsive efficiency of the gas turbine engine. However, for larger fan diameters, ducted turbofan engines may also require larger nacelles, which can lead to encapsulation problems, weight and load issues, etc. The inventors of this disclosure have discovered that the dimensions of the nacelle for an engine including a larger diameter fan can be advantageously reduced by an amount determined by an optimally sized engine controller to achieve the goal of reducing the nacelle height (i.e., an engine controller with minimal radial height and without unacceptable weight and nacelle encapsulation problems).

[0053] The most volumetrically efficient design for an engine controller is a cubic shape, which maximizes internal volume and minimizes the amount of material required for the engine controller housing, thereby reducing the overall weight of the engine controller. However, the inventors of this disclosure have discovered that a relatively low radial thickness nacelle, which may be necessary to power engines including fans with large fan diameters, can result in an excessively large radial range. Conversely, the inventors have discovered that an engine controller with a smaller radial range, within the scope defined herein, can facilitate the aforementioned relatively low radial thickness nacelle without resulting in an unnecessarily thin and heavy engine controller. Therefore, as described above, there is a trade-off between the desired reduction in radial height and the avoidance of excessive weight increase.

[0054] Using this relationship, the inventors discovered that the number of suitable or feasible turbofan engine designs combining a fan with a relatively large fan diameter and an engine controller with a desired size can be significantly reduced, simultaneously satisfying propulsion efficiency requirements and addressing engine controller packaging and weight issues. Therefore, the discovered relationship not only defines the optimal controller design but also facilitates a faster downward selection of the design to be considered when developing a turbofan engine. This benefit allows for a deeper understanding of the requirements of a given turbofan engine before specific technology, integration, and system requirements are fully developed. It avoids late-stage redesign. The desired relationship is expressed by the following equation (1):

[0055] Equation (1): ;

[0056] in It is the normalized radius of the engine controller. It is the radial height of the engine controller. K is the radius of the inner surface of the engine compartment along the radial direction of the engine, and K is a relevant constant.

[0057] It is worth noting that the normalized radius ( ) is the inner surface radius ( The ratio of the volume of the engine controller to the cube root of its total volume (V) (i.e., Normalized radius () The normalized radius ( ) can be a non-cubic shape, relative to the scaling radius of one side of a characteristic single cubic box having the same total volume as the engine controller. In this way, the normalized radius ( This reflects the baseline of the radial range of the engine controller if volumetric efficiency design is the driving factor in the engine controller design. Furthermore, as mentioned above, K is a correlation constant. The correlation constant K reflects the upper bound, in which the benefits of equation (1) are considered to still hold. It is worth noting that, in addition to the radial height ( ) and total volume ( The total surface area (A) of the top surface of the engine controller may also be a design metric for the engine controller and may further affect, for example, the engine controller’s ability to dissipate heat during engine operation.

[0058] Table 1 provides the range of variables defining equation (1) and argues that it provides the benefits mentioned above:

[0059]

[0060] Now for reference Figure 6A , 6B 7. Data for an exemplary gas turbine engine is provided according to one or more exemplary embodiments of this disclosure. Specifically, Figure 6A and 6B Provided including corresponding Figure 7 The table shows the values ​​of the shaded areas indicated in the chart. Specifically, Figure 6A Provided including corresponding Figure 7 The table shows the values ​​of the first region 206. Figure 6B Provided including corresponding Figure 7 The table shows the values ​​for region 208 in the second area. Figure 6A and 6B In the table, "box #" refers to the number of separate housings for the engine controller (see, for example, see...). Figure 2 and 4 Single-casing embodiments and Figure 5 (Double-casing embodiment); "Type" refers to whether the engine controller is a box-type design ("TRAD."; see Figure 2), or whether the engine controller has a curved profile (“curved”; see Figure 4 ), or whether the engine controller has multiple housings (“separate”; see Figure 5 ).

[0061] Figure 7 This is a graph 200 of a gas turbine engine according to one or more exemplary embodiments of the present disclosure, showing the relationship between the normalized radius of the engine controller on the x-axis 202 and the ratio of the radial height of the engine controller to the inner surface radius on the y-axis 204. A first region 206 on the graph reflects a first range, wherein the normalized radius ( The value is between 1.25 and 8, and K equals 40%. The second region 208 on the graph reflects the second range, where the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

[0062] In this way, it should be understood that, according to the exemplary aspects of this disclosure, the first range can typically capture turbofan engines with a relatively wide range of fan diameters and including conformal engine controllers. It should also be understood that the second range can typically capture a more tailored range of fan diameters typically associated with narrow-body aircraft (e.g., fan diameters between 70 and 88). It should be understood that, due to the size of narrow-body aircraft, obtaining conformal engine controllers for these engines can often be more difficult.

[0063] Further aspects are provided by the following topics:

[0064] A gas turbine engine defining axial and radial directions includes: a turbine having a compressor section, a combustion section, and a turbine section in series flow sequence; a fan section including a fan rotatable by the turbine; a nacelle surrounding the fan; and an engine controller positioned within the nacelle, wherein the nacelle defines an inner surface radius of the engine controller along the radial direction. ), wherein the engine controller defines a radial height along the radial direction ( ), total volume ( ) and normalized radius ( ), wherein the normalized radius ( ) is the inner surface radius ( ) and the total volume ( The ratio of the cube roots of ), where these parameters are related by the following equation:

[0065] ,

[0066] The normalized radius ( The value is between 1.25 and 8 and K equals 40%, or the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

[0067] According to one or more of these clauses, the gas turbine engine, wherein the normalized radius ( The value is between 1.25 and 8, and K equals 40%.

[0068] According to one or more of these clauses, the gas turbine engine, wherein the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

[0069] A gas turbine engine according to one or more of these clauses, wherein the engine controller includes a top surface defining a surface area, wherein the surface area is greater than or equal to 254 square inches and less than or equal to 2043 square inches.

[0070] According to one or more of these clauses, the gas turbine engine, wherein the inner surface radius ( (17 inches or greater and 84 inches or less)

[0071] According to one or more of these clauses, the gas turbine engine, wherein the inner surface radius ( (35 inches or greater and 44 inches or less)

[0072] The gas turbine engine according to one or more of these clauses, wherein the total volume ( (500 cubic inches or more and 3000 cubic inches or less)

[0073] The gas turbine engine according to one or more of these clauses, wherein the total volume ( (Greater than or equal to 900 cubic inches and less than or equal to 1500 cubic inches)

[0074] According to one or more of these clauses, the radial height ( (Greater than or equal to 0.5 inches and less than or equal to 8 inches)

[0075] According to one or more of these clauses, the radial height ( (1 inch or more and 4 inches or less)

[0076] A gas turbine engine according to one or more of these clauses, wherein the engine controller includes a housing that defines a curved profile in a reference plane perpendicular to the axial direction.

[0077] According to one or more of these clauses, the gas turbine engine, wherein the engine controller includes one or more circuit boards, and wherein the one or more circuit boards define a curved profile in the reference plane perpendicular to the axial direction.

[0078] According to one or more of these clauses, the gas turbine engine, wherein the engine controller comprises a plurality of discrete boxes spaced apart along the circumferential direction of the gas turbine engine, along the axial direction of the gas turbine engine, or both.

[0079] An engine controller for defining an axial and radial direction of a gas turbine engine, the gas turbine engine having a nacelle surrounding a fan, wherein the nacelle defines the inner surface radius of the engine controller along the radial direction. The engine controller includes: a housing that defines an engine casing, the engine casing having an overall volume ( When installed in the gas turbine engine, the engine controller defines a radial height along the radial direction. ), and when installed in the gas turbine engine, the normalized radius is defined ( ), wherein the normalized radius ( ) is the inner surface radius ( ) and the total volume ( The ratio of the cube roots of ), where these parameters are related by the following equation:

[0080] ,

[0081] The normalized radius ( The value is between 1.25 and 8 and K equals 40%, or the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

[0082] According to one or more of these clauses, the engine controller, wherein the normalized radius ( The value is between 1.25 and 8, and K equals 40%.

[0083] According to one or more of these clauses, the engine controller, wherein the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

[0084] An engine controller according to one or more of these clauses, wherein the engine controller includes a top surface defining a surface area, wherein the surface area is greater than or equal to 254 square inches and less than or equal to 2043 square inches.

[0085] The engine controller according to one or more of these clauses, wherein the total volume ( (500 cubic inches or more and 3000 cubic inches or less)

[0086] According to one or more of these clauses, the engine controller, wherein the radial height ( (Greater than or equal to 0.5 inches and less than or equal to 8 inches)

[0087] An engine controller according to one or more of these clauses, wherein when installed in the gas turbine engine, the housing defines a curved profile in a reference plane perpendicular to the axial direction.

[0088] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any incorporated methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A gas turbine engine defining axial and radial directions, characterized in that, include: A turbine having a compressor section, a combustion section and a turbine section in series flow sequence; A fan section, the fan section including a fan capable of being rotated by the turbine; The cabin surrounds the fan; and An engine controller, the engine controller being positioned within the engine compartment, wherein the engine compartment defines the inner surface radius of the engine controller along the radial direction. ), wherein the engine controller defines a radial height along the radial direction ( ), total volume ( ) and normalized radius ( ), wherein the normalized radius ( ) is the inner surface radius ( ) and the total volume ( The ratio of the cube roots of ), where these parameters are related by the following equation: ， The normalized radius ( The value is between 1.25 and 8 and K equals 40%, or the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

2. The gas turbine engine according to claim 1, characterized in that, The engine controller includes a top surface that defines a surface area greater than or equal to 254 square inches and less than or equal to 2043 square inches.

3. The gas turbine engine according to claim 1, characterized in that, The inner surface radius ( (17 inches or greater and 84 inches or less) 4. The gas turbine engine according to claim 1, characterized in that, The inner surface radius ( (35 inches or greater and 44 inches or less) 5. The gas turbine engine according to claim 1, characterized in that, The total volume ( (500 cubic inches or more and 3000 cubic inches or less) 6. The gas turbine engine according to claim 1, characterized in that, The total volume ( (Greater than or equal to 900 cubic inches and less than or equal to 1500 cubic inches) 7. The gas turbine engine according to claim 1, characterized in that, The radial height ( (Greater than or equal to 0.5 inches and less than or equal to 8 inches) 8. The gas turbine engine according to claim 1, characterized in that, The radial height ( (1 inch or more and 4 inches or less) 9. The gas turbine engine according to claim 1, characterized in that, The engine controller includes a housing that defines a curved profile in a reference plane perpendicular to the axial direction.

10. The gas turbine engine according to claim 9, characterized in that, The engine controller includes one or more circuit boards, and the one or more circuit boards define a curved profile in the reference plane perpendicular to the axial direction.

11. The gas turbine engine according to claim 1, characterized in that, The engine controller includes a plurality of discrete boxes spaced apart along the circumferential direction of the gas turbine engine, along the axial direction of the gas turbine engine, or both.

12. An engine controller for defining an axial and radial direction of a gas turbine engine, the gas turbine engine having a nacelle surrounding a fan, wherein the nacelle defines the inner surface radius of the engine controller along the radial direction. ), characterized in that, The engine controller includes: Housing, the housing defining the casing, the casing having a total volume ( When installed in the gas turbine engine, the engine controller defines a radial height along the radial direction. ), and when installed in the gas turbine engine, the normalized radius is defined ( ), wherein the normalized radius ( ) is the inner surface radius ( ) and the total volume ( The ratio of the cube roots of ), where these parameters are related by the following equation: ， The normalized radius ( The value is between 1.25 and 8 and K equals 40%, or the normalized radius ( The value is between 2.75 and 4.5 and K equals 65%.

13. The engine controller according to claim 12, characterized in that, The engine controller includes a top surface that defines a surface area greater than or equal to 254 square inches and less than or equal to 2043 square inches.

14. The engine controller according to claim 12, characterized in that, The total volume ( (500 cubic inches or more and 3000 cubic inches or less) 15. The engine controller according to claim 12, characterized in that, The radial height ( (Greater than or equal to 0.5 inches and less than or equal to 8 inches) 16. The engine controller according to claim 12, characterized in that, When installed in the gas turbine engine, the housing defines a curved profile in a reference plane perpendicular to the axial direction.

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