Aircraft air conditioning component assembly and assembly method

Abstract

The present disclosure relates to an aircraft air conditioning assembly and an assembly method. An aircraft air conditioning assembly includes: an air conditioning assembly configured to discharge heat; and an external panel positioned adjacent to the air conditioning assembly. The external panel includes an opening defined therein, a first side facing the air conditioning assembly, and a second side defining an external surface configured to communicate with a free stream airflow. At least a portion of the air conditioning assembly is disposed within the opening to facilitate transfer of heat from the air conditioning assembly to the free stream airflow.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft environmental control systems and, more particularly, to air conditioning assemblies and luggage compartment assemblies having improved heat dissipation capabilities. Background Art

[0002] At least some known aircraft include a ram air system that provides ram air to at least one air conditioning component of an aircraft environmental control system (ECS). In some known aircraft, the air conditioning component is located in a luggage compartment of the aircraft along with other aircraft components. The air conditioning component uses ram air to provide cooling for high temperature aerodynamic air delivered to the aircraft passenger cabin. However, the ram air cannot absorb all of the internal heat, and therefore, heat may be transferred to components in the luggage compartment and surrounding aircraft structures. At least some aircraft include a layer of insulation around the air conditioning component to reduce heat discharge from the air conditioning component into the luggage compartment. However, such insulation increases the overall weight and space envelope of the aircraft and may have a limited service life.

[0003] This section is intended to introduce the reader to various aspects of the art that may be related to various aspects of the present disclosure, which are described and / or claimed below. It is believed that this discussion helps to provide the reader with background information to promote a better understanding of various aspects of the present disclosure. Therefore, it should be understood that these statements should be read from this perspective, and not as an admission of prior art. Summary of the invention

[0004] In one aspect, an aircraft air conditioning assembly is provided. The assembly includes an air conditioning assembly configured to discharge heat, and an external panel positioned proximate to the air conditioning assembly. The external panel includes an opening defined therein, a first side facing the air conditioning assembly, and a second side defining an external surface configured to communicate with a free stream airflow. At least a portion of the air conditioning assembly is disposed within the opening to facilitate transfer of heat from the air conditioning assembly to the free stream airflow.

[0005] In another aspect, an aircraft is provided. The aircraft includes a luggage compartment defined on a side of the aircraft, the luggage compartment including an inner compartment. An air conditioning assembly is located in the inner compartment, and the air conditioning assembly is configured to discharge heat. An outer panel is positioned adjacent to the air conditioning assembly and at least partially defines the inner compartment. The outer panel includes an opening defined therein, a first side facing the air conditioning assembly, and a second side defining an outer surface of the aircraft configured to communicate with a free stream airflow. At least a portion of the air conditioning assembly is disposed within the opening to facilitate transfer of heat from the air conditioning assembly to the free stream airflow.

[0006] In another aspect, a method of assembling an aircraft is provided. The method includes defining a luggage compartment on an underside of the aircraft, wherein the luggage compartment includes an inner compartment; positioning an air conditioning assembly in the inner compartment, wherein the air conditioning assembly is configured to discharge heat; and positioning an outer panel proximate the air conditioning assembly to at least partially define the inner compartment. The outer panel includes an opening defined therein, and the outer panel is positioned such that a first side thereof faces the air conditioning assembly and such that a second side thereof defines an outer surface of the aircraft configured to communicate with a free stream airflow. The method also includes disposing at least a portion of the air conditioning assembly within the opening to facilitate heat transfer from the air conditioning assembly to the free stream airflow.

[0007] There are various improvements to the features noted with respect to the above aspects of the disclosure. Other features may also be incorporated into the above aspects of the disclosure. These improvements and additional features may exist alone or in any combination. For example, the various features discussed below with respect to any illustrated embodiment of the disclosure may be incorporated into any of the above aspects of the disclosure alone or in any combination. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 is a schematic diagram of an example aircraft.

[0009] Figure 2 yes Figure 1 A bottom view of a portion of the aircraft is shown.

[0010] Figure 3 yes Figure 2 A cross-sectional view of a portion of an aircraft is shown and taken along line 3 - 3 , and the portion of the aircraft includes an example aircraft air conditioning assembly.

[0011] Figure 4 Shows Figure 3 sectional view of an aircraft air conditioning assembly as shown in FIG.

[0012] Figure 5 yes Figure 2 A schematic cross-sectional view of a portion of an aircraft including an example sealing system is shown and taken along line 5 - 5 .

[0013] Figure 6 Shows Figure 5 Schematic cross-sectional view of the illustrated and including additional sealing systems.

[0014] Figure 7 Shows Figure 5 Schematic cross-sectional view of the illustrated and including additional sealing systems.

[0015] Figure 8 Shows Figure 5 Shown is and includes a schematic cross-sectional view of an additional sealing system in a first operating mode.

[0016] Fig. 9 Shows Figure 5 Shown is and includes a schematic cross-sectional view of an additional sealing system in a second mode of operation.

[0017] Corresponding reference characters indicate corresponding parts throughout the drawings. DETAILED DESCRIPTION

[0018] The described embodiments relate to an air conditioning assembly and a luggage compartment assembly with improved heat dissipation capabilities. As described herein, the assembly includes an air conditioning assembly configured to discharge heat, and an external panel positioned adjacent to the air conditioning assembly. The external panel has an opening defined therein, which provides a flow communication path between the luggage compartment and the surrounding environment. At least a portion of the air conditioning assembly is disposed in the opening so that the air conditioning assembly is exposed to the surrounding environment. The portion of the air conditioning assembly disposed in the opening does not have an intermediate layer of insulating material between the air conditioning assembly and the external panel. In one implementation, the air conditioning assembly has a bottom wall that extends through the opening to be directly flow-connected with the surrounding environment. The bottom wall may have an airfoil cross-sectional shape to facilitate maintaining the aerodynamic efficiency of the aircraft. In either implementation, the heat generated by the air conditioning assembly can be discharged to the surrounding environment in an efficient, space-saving and weight-reducing manner, thereby enhancing the heat dissipation capabilities of the internal flow.

[0019] As used herein, an element or step stated in the singular and preceded by the word "a" or "an" should be understood as not excluding multiple elements or steps, unless such exclusion is explicitly stated. In addition, reference to "an exemplary implementation" or "an implementation" of the present disclosure is not intended to be interpreted as excluding the existence of additional implementations that also include the described features.

[0020] Figure 1 1 is a schematic diagram of an example aircraft 100. Aircraft 100 includes a pressurized area 102 and an unpressurized area 104. Pressurized area 102 includes, but is not limited to, a cockpit 106 and a passenger cabin 108. Unpressurized area 104 includes, but is not limited to, a luggage compartment 112 defined on an underside 114 of aircraft 100. Luggage compartment 112 has an interior space 116, and an air conditioning assembly 118 is located in interior space 116. In operation, air conditioning assembly 118 receives airflow from, for example, an engine, an auxiliary power unit, or an electric compressor (none of which is shown) on aircraft 100. Air conditioning assembly 118 then cools the airflow and exhausts the cooled airflow for distribution within pressurized area 102. Thus, air conditioning assembly 118 generates and dissipates heat during its operation.

[0021] Figure 2 is a bottom view of a portion of aircraft 100, and Figure 33-3 is a cross-sectional view of a portion of the aircraft 100 taken along line 3-3. The aircraft 100 includes an exterior panel 120 proximate to an air conditioning assembly 118 located within the baggage compartment 112. The exterior panel 120 has an opening 122 defined therein. The exterior panel 120 also has a first side 124 facing the air conditioning assembly 118 and a second side 126 defining an exterior surface 128 of the aircraft 100. The first side 124 faces the air conditioning assembly 118, and it extends in a direction that at least a portion of the air conditioning assembly 118 faces the first side 124. The exterior surface 128 is in communication with a free stream airflow 130 directed through the exterior panel 120. The free stream airflow 130 is defined by an ambient environment 132 defined by the exterior of the aircraft 100. In addition, when the aircraft 100 is moving, the speed and cooling capacity of the free stream airflow 130 are generally directly proportional to the speed of the aircraft 100, and the free stream airflow 130 is directed through the exterior panel 120 in a generally rearward direction (RWD). As used herein, the term “in close proximity” refers to when the exterior panel 120 is in contact with or minimally spaced from any portion of the air conditioning assembly 118 .

[0022] The air conditioning assembly 118 includes a heat exchanger 134, and a plurality of conduits 135 are in fluid communication with the heat exchanger 134. The airflow is directed to the heat exchanger 134 via the one or more conduits 135 to facilitate the transfer of heat between the airflows, and the airflow is discharged from the heat exchanger 134 to be distributed in the pressurized area 102 ( Figure 1 13. The heat exchanger 134 has a top side 136, a bottom side 138, and a plurality of lateral sides 140 extending therebetween. As described above, the air conditioning assembly 118 generates heat during its operation. For example, Figure 3 As shown, heat 142 is exhausted from each side 136 , 138 , and 140 of the air conditioning assembly 118 .

[0023] At least a portion of the air conditioning assembly 118 is disposed within the opening 122 of the exterior panel 120 to facilitate transfer of heat 142 from the air conditioning assembly 118 to the free stream airflow 130. For example, a bottom side 138 of the heat exchanger 134 and at least a portion of the duct 135 are disposed within the opening 122 and are directly exposed to the ambient environment 132. Thus, the air conditioning assembly 118 and the duct 135 are positioned to discharge heat 142 directly to the free stream airflow 130. Furthermore, the bottom side 138 and a portion of the duct 135 are disposed substantially flush with the exterior surface 128 of the aircraft 100. In this manner, the bottom side 138 and a portion of the duct 135 are exposed to the ambient environment 132 while still substantially maintaining the aerodynamic efficiency of the aircraft 100.

[0024] In one implementation, a layer of insulating material 144 extends over at least a portion of the heat exchanger 134. For example, as described above, the bottom side 138 of the heat exchanger 134 is directly exposed to the ambient environment 132 to facilitate heat discharge to the free stream airflow 130. However, the remaining sides of the heat exchanger 134, such as the top side 136 and the longitudinal sides 140, are covered by the layer 144 to help reduce heat transfer between the air conditioning assembly 118 and the interior cabin 116 of the luggage compartment 112. In this way, electronic or other components (not shown) within the luggage compartment 112 and the aircraft structure are protected from exposure to increased heat and temperature changes. Examples of insulating materials include, but are not limited to, fiberglass materials, such as in a blanket form, or closed-cell foam materials, such as polyvinylidene fluoride or polyvinylidene difluoride (PVDF).

[0025] Reference now Figure 4 , the air conditioning assembly 118 includes a bottom wall 146 disposed on the bottom side 138 of the heat exchanger 134. At least a portion of the bottom wall 146 extends through the opening 122 in the outer panel 120 to locate the exterior of the luggage compartment 112. That is, in one implementation, the bottom wall 146 is joined to the first side 124 of the outer panel 120, and a portion of the bottom wall 146 extends from the first side 124 through the opening 122. Alternatively, the bottom wall 146 is formed separately from the heat exchanger 134 and joined to the second side 126 of the outer panel 120. In either implementation, the bottom wall 146 is oriented to be in flow communication with the free stream airflow 130 to facilitate defining a thermal communication path for the heat 142 discharged from the air conditioning assembly 118. In addition, the opening 122 is at least partially defined by the front edge 148 and the rear edge 150 of the outer panel 120. In either implementation, the bottom wall 146 extends between the front edge 148 and the rear edge 150t to facilitate sealing of the interior compartment 116 from the surrounding environment 132 .

[0026] Additionally, exposing bottom wall 146 to free stream airflow 130 may help reduce the aerodynamic efficiency of aircraft 100 (eg, Figure 1146 ). Thus, the portion of the bottom wall 146 that extends through the opening 122 has an airfoil cross-sectional shape to reduce the drag caused by the bottom wall 146 to the aircraft 100 during flight. The shape of the bottom wall 146 helps to define an open space 152 between the heat exchanger 134 and the bottom wall 146 and between the duct 135 and the bottom wall 146. In one implementation, the open space 152 contains air that receives heat 142 from the heat exchanger 134 and facilitates its passage through the bottom wall 146 to be transferred to the free stream airflow 130. Alternatively, a thermally conductive material 154 is located between the air conditioning assembly 118 and the bottom wall 146, and between the duct 135 and the bottom wall 146. The thermally conductive material 154 helps to enhance the transfer of heat from the air conditioning assembly 118 and the duct 135 to the free stream airflow 130. Example thermally conductive materials include, but are not limited to, thermally conductive foam materials, heat pipes, or non-structural lightweight metal materials (e.g., aluminum).

[0027] Figure 5 1 is a schematic cross-sectional view of a portion of an aircraft 100 including an example sealing system 156, wherein an outer panel 120 provides a primary load path for mounting an air conditioning assembly 118. The sealing system 156 is configured to restrict the inflow of free stream airflow 130 and debris (not shown) through the opening 122. In an example implementation, the outer panel 120 includes an indent 158, and the air conditioning assembly 118 includes a flange 160 sized to be received within the indent 158. For example, the indent 158 ​​and the flange 160 are sized such that an outer surface 162 of the air conditioning assembly 118 is substantially flush with an outer surface 128 of the outer panel 120 at an interface 164 defined therebetween.

[0028] The sealing system 156 includes at least one sealing member positioned around the periphery of the opening 122. For example, the sealing system 156 includes a first sealing member 166 and a second sealing member 168 positioned between the air conditioning assembly 118 and the outer panel 120. The outer panel 120 includes a side edge 170 that is spaced apart from the longitudinal side 140 of the air conditioning assembly 118 so as to define a cavity 172 therebetween. The first sealing member 166 is positioned within the cavity 172 and is preloaded before being positioned within the cavity 172 to facilitate sealing the interior compartment 116 of the luggage compartment 112 from the surrounding environment 132. The second sealing member 168 is joined to the air conditioning assembly 118 and the outer panel 120 to facilitate sealing the cavity 172. That is, the second sealing member 168 is joined to the longitudinal direction 140 of the air conditioning assembly 118 and extends through the cavity 172 to further join to the first side 124 of the outer panel 120. The fastener 174 extends through the second sealing member 168, the outer panel 120, and the flange 160 of the air conditioning assembly 118 to facilitate mounting the air conditioning assembly 118 on the aircraft 100. In this way, the second sealing member 168 is statically fixed between the air conditioning assembly 118 and the outer panel 120 to facilitate enhancing the seal between the interior cabin 116 of the luggage compartment 112 and the surrounding environment 132. In an alternative implementation, the second fastener is insertable and easily removed and installed from the outside of the aircraft 100. In this way, when the air conditioning assembly 118 is detached from the outer panel 120, the luggage compartment 116 can be accessed from the outside of the aircraft 100.

[0029] First sealing member 166 and second sealing member 168 are made of any material that enables aircraft 100 to function as described herein. Example sealing materials include, but are not limited to, elastomeric materials. When made of elastomeric materials, first sealing member 166 and second sealing member 168 can accommodate relative movement between air conditioning assembly 118 and exterior panel 120.

[0030] Figure 6 Shows Figure 5 1 and includes an additional sealing system 176. The aircraft 100 includes a lower panel 178 and an attachment mechanism 180 engaged between the air conditioning assembly 118 and the lower panel 178. The attachment mechanism 180 provides a primary load path for mounting the air conditioning assembly 118 on the aircraft 100, thereby reducing the load caused by the air conditioning assembly 118 on the outer panel 120 when attached therebetween. In this way, the air conditioning assembly 118 remains substantially stationary relative to the lower panel 178.

[0031] The air conditioning assembly 118 is spaced apart from the outer panel 120 such that a gap 182 is defined between the flange 160 of the air conditioning assembly 118 and the side edge 170 of the outer panel 120. The first sealing member 166 is located within the gap 182, and the second sealing member 184 and the third sealing member 186 are located on opposite sides of the gap 182. The second sealing member 184 is adapted to seal the gap 182 and also accommodate movement of the outer panel 120 relative to the air conditioning assembly 118. For example, a layer 188 of a low friction coating material is applied to the flange 160, and the second sealing member 184 has a sacrificial layer 190 of a material formed thereon. In operation, the outer panel 120 is translatable relative to the air conditioning assembly 118 due to the sliding interface between the layer 188 of the low friction coating material and the sacrificial layer 190. Therefore, the sealing system 176 is able to accommodate a greater degree of relative movement between the air conditioning assembly 118 and the outer panel 120.

[0032] Figure 7 Shows Figure 5 A schematic cross-sectional view of an additional sealing system 192 is shown, wherein the outer panel 120 provides a primary load path for the installation of the air conditioning assembly 118. The air conditioning assembly 118 is spaced apart from the outer panel 120, thereby defining a gap 182 between the flange 160 of the air conditioning assembly 118 and the side edge 170 of the outer panel 120. In addition, the flange 160 includes a lip member 194 oriented to extend into the interior compartment 116 of the luggage compartment 112. The sealing system 192 includes a sealing member 196 that is located within the gap 182 and has a first portion 198 and a second portion 200 that are positioned on opposite sides of the gap 182. The second portion 200 of the sealing member 196 is engaged to and surrounds at least a portion of the lip member 194. In this way, the lip member 194 helps to maintain the sealing member 196 in a proper position relative to the air conditioning assembly 118 and the outer panel 120.

[0033] Figure 8 Shows Figure 5 2 and includes a schematic cross-sectional view of an additional sealing system 202 in a first operating mode, Fig. 9 An additional sealing system 202 is shown in a second operating mode. The air conditioning assembly 118 and the outer panel 120 are spaced apart from each other such that a gap 204 is defined therebetween. The sealing system 202 includes a spring-seal member 206 positioned within the gap 204. When in the first operating mode, the spring-seal member 206 is preloaded within the gap 204 so that the spring-seal member 206 can accommodate relative movement between the air conditioning assembly 118 and the outer panel 120. For example, Fig. 9As shown, when the outer panel 120 moves away from the air conditioning assembly 118, the spring sealing member 206 can expand to accommodate the increase in the size of the gap 204. The spring sealing member 206 can be made of any material that enables the sealing system 202 to function as described herein. Example materials include, but are not limited to, shape memory alloy materials. In an alternative implementation, the spring sealing member 206 is a biasing device that is at least partially encapsulated by an elastomeric material.

[0034] Furthermore, the present disclosure includes embodiments according to the following items:

[0035] Item 1. An aircraft air conditioning component assembly, comprising:

[0036] an air conditioning assembly (118) configured to reject heat; and

[0037] An outer panel (120) is positioned adjacent to an air conditioning assembly (118), the outer panel (120) including an opening (122) defined therein, and the outer panel (120) includes a first side (124) facing the air conditioning assembly (118) and a second side (126) defining an outer surface (128) configured to communicate with a free flow airflow (130), wherein at least a portion of the air conditioning assembly (118) is disposed within the opening (122) to facilitate transfer of heat from the air conditioning assembly (118) to the free flow airflow (130).

[0038] Item 2. An assembly according to Item 1, wherein the air conditioning component (118) includes a shell (134), the shell (134) includes a top side (136) and multiple longitudinal sides (140), and the assembly also includes a layer of insulating material (144) extending on the top side (136) and the multiple longitudinal sides (140).

[0039] Item 3. The assembly of Item 2, wherein the layer of insulating material (144) does not extend between the air conditioning assembly (118) and the exterior panel (120).

[0040] Item 4. The assembly of Item 1, wherein the air conditioning assembly (118) includes a bottom wall (146), wherein at least a portion of the bottom wall (146) extends through the opening (122) of the outer panel (120).

[0041] Item 5. The assembly of Item 4, wherein the portion of the bottom wall (146) extending through the opening (122) has an airfoil cross-sectional shape.

[0042] Item 6. The assembly of Item 4, further comprising a thermally conductive material (154) located between the air conditioning assembly (118) and the bottom wall (146).

[0043] Item 7. The assembly of Item 1 further includes a sealing member (166) located between the air conditioning assembly (118) and the exterior panel (120), wherein the sealing member (166) is configured to limit the flow of free flow airflow (130) passing through the opening (122) and flowing toward the air conditioning assembly (118).

[0044] Item 8. The assembly of Item 7, wherein the sealing member (166) is made of a material configured to accommodate relative movement between the air conditioning assembly (118) and the exterior panel (120).

[0045] Item 9. An aircraft (100), comprising:

[0046] a luggage compartment (112) defined on an underside (114) of the aircraft (100), the luggage compartment (112) including an interior compartment (116);

[0047] an air conditioning assembly (118) located within the interior cabin (116), the air conditioning assembly (118) being configured to discharge heat; and

[0048] An exterior panel (120) is positioned proximate to an air conditioning assembly (118) and at least partially defines an interior cabin (116), the exterior panel (120) including an opening (122) defined therein, and the exterior panel (120) includes a first side (124) facing the air conditioning assembly (118) and a second side (126) defining an aircraft exterior surface (128) configured to communicate with a free stream airflow (130), wherein at least a portion of the air conditioning assembly (118) is disposed within the opening (122) to facilitate transfer of heat from the air conditioning assembly (118) to the free stream airflow (130).

[0049] Clause 10. The aircraft (100) of clause 9, wherein the exterior panel (120) is a baggage compartment door or a fairing panel of the aircraft.

[0050] Item 11. An aircraft (100) according to Item 9, wherein the air conditioning assembly (118) includes an outer shell (134), the outer shell includes a top side (136) and multiple longitudinal sides (140), and the aircraft also includes a layer of insulating material (144) extending over the top side (136) and the multiple longitudinal sides (140).

[0051] Item 12. The aircraft (100) of Item 11, wherein the layer of thermal insulation material (144) does not extend between the air conditioning assembly (118) and the exterior panel (120).

[0052] Item 13. The aircraft (100) of Item 9, wherein the air conditioning assembly (118) includes a bottom wall (146), wherein at least a portion of the bottom wall (146) extends through the opening (122) in the outer panel (120).

[0053] Item 14. The aircraft (100) of Item 13, wherein the portion of the bottom wall (146) extending through the opening (122) has an airfoil cross-sectional shape.

[0054] Item 15. The aircraft (100) of Item 13, further comprising a thermally conductive material (154) located between the air conditioning assembly (118) and the bottom wall (146).

[0055] Item 16. The aircraft (100) of Item 9, further comprising a sealing member (166) disposed relative to the opening (122) and configured to conform to a portion of the air conditioning assembly (118) disposed within the opening (122).

[0056] Item 17. A method of assembling an aircraft (100), the method comprising:

[0057] A luggage compartment (112) is defined on an underside (114) of the aircraft (100), wherein the luggage compartment (112) includes an interior compartment (116);

[0058] positioning an air conditioning assembly (118) within the interior cabin (116), wherein the air conditioning assembly (118) is configured to discharge heat;

[0059] positioning an exterior panel (120) proximate to an air conditioning assembly (118) to at least partially define an interior cabin (116), wherein the exterior panel (120) includes an opening (122) defined therein, and wherein the exterior panel (120) is positioned such that a first side (124) thereof faces the air conditioning assembly (118) and such that a second side (126) thereof defines an exterior surface (128) of the aircraft configured to communicate with a free stream airflow (130); and

[0060] At least a portion of the air conditioning assembly (118) is disposed within the opening (122) to facilitate heat transfer from the air conditioning assembly (118) to the free flow airflow (130).

[0061] Item 18. The method of Item 17, further comprising extending the layer of insulating material (144) across the air conditioning component (118), wherein the layer of insulating material (144) does not extend between the air conditioning component (118) and the exterior panel (120).

[0062] Item 19. A method according to Item 17, wherein the air conditioning assembly (118) includes a bottom wall (146), and the method further includes orienting the air conditioning assembly (118) such that at least a portion of the bottom wall (146) extends through an opening (122) in the outer panel (120).

[0063] Item 20. The method according to Item 17 further includes disposing a sealing member (166) between the air conditioning assembly (118) and the external panel (120), the sealing member (166) being configured to conform to a portion of the air conditioning assembly (118) disposed within the opening (122).

[0064] This written description uses examples to disclose various implementations, including the best mode, and also enables those skilled in the art to practice the various implementations, including making and using any device or system and performing any combined methods. The patentable scope of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. If such other examples have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims, they are intended to be within the scope of the claims.

Claims

1. An aircraft air conditioning component assembly, comprising: an air conditioning assembly (118) configured to discharge heat; and an exterior panel (120) positioned proximate to the air conditioning assembly (118), the exterior panel (120) including an opening (122) defined therein, and the exterior panel (120) including a first side (124) facing the air conditioning assembly (118) and a second side (126) defining an exterior surface (128) configured to communicate with a free stream airflow (130), The air conditioning assembly (118) includes a bottom wall (146), which is disposed within the opening (122) and extends through the opening (122) so that the bottom wall protrudes from the outer panel, and at least a portion of the bottom wall (146) is oriented obliquely relative to the free flow airflow to facilitate the transfer of heat from the air conditioning assembly (118) to the free flow airflow (130).

2. The assembly according to claim 1, wherein: The air conditioning assembly (118) includes a housing (134) including a top side (136) and a plurality of longitudinal sides (140), the assembly further including a layer of thermal insulation material (144) extending over the top side (136) and the plurality of longitudinal sides (140).

3. The assembly according to claim 2, wherein: The layer of thermal insulation material (144) does not extend between the air conditioning assembly (118) and the exterior panel (120).

4. The assembly according to claim 1, wherein: The portion of the bottom wall (146) extending through the opening (122) has an airfoil cross-sectional shape.

5. The assembly according to claim 1, wherein: An open space is defined between the air conditioning assembly (118) and the bottom wall (146), and the assembly further includes a thermally conductive material (154) located within the open space.

6. The assembly according to any one of claims 1 to 3, further comprising a sealing member (166) located between the air conditioning assembly (118) and the outer panel (120), wherein: The sealing member (166) is configured to restrict free-flow airflow (130) flowing through the opening (122) and toward the air conditioning assembly (118).

7. The assembly according to claim 6, wherein: The sealing member (166) is made of a material configured to accommodate relative movement between the air conditioning assembly (118) and the exterior panel (120).

8. The assembly according to any one of claims 1 to 3, included on an aircraft (100), the aircraft comprising: a luggage compartment (112) defined on an underside (114) of the aircraft (100), the luggage compartment (112) including an inner compartment (116); Wherein, the air conditioning component (118) is located in the inner cabin (116).

9. The assembly according to claim 8, included on an aircraft (100), wherein: The exterior panel (120) is a baggage compartment door or a fairing panel of the aircraft.

10. A method of assembling an aircraft (100), the method comprising: A luggage compartment (112) is defined on an underside (114) of the aircraft (100), wherein the luggage compartment (112) includes an interior compartment (116); Positioning an air conditioning assembly (118) within the interior cabin (116), wherein the air conditioning assembly (118) is configured to discharge heat; positioning an exterior panel (120) proximate the air conditioning assembly (118) to at least partially define the interior cabin (116), wherein the exterior panel (120) includes an opening (122) defined therein, and wherein the exterior panel (120) is positioned such that a first side (124) thereof faces the air conditioning assembly (118) and such that a second side (126) thereof defines an exterior surface (128) of the aircraft configured to communicate with a free stream airflow (130); and A bottom wall (146) of the air conditioning assembly (118) is disposed within the opening (122), the bottom wall extending through the opening (122) such that the bottom wall protrudes from the outer panel, and at least a portion of the bottom wall (146) is oriented obliquely relative to the free flow airflow to facilitate heat transfer from the air conditioning assembly (118) to the free flow airflow (130).

11. The method of claim 10, further comprising extending a layer of thermal insulation material (144) across the air conditioning assembly (118), wherein: The layer of thermal insulation material (144) does not extend between the air conditioning assembly (118) and the exterior panel (120).

12. The method of any one of claims 10 to 11, further comprising disposing a sealing member (166) between the air conditioning assembly (118) and the exterior panel (120), the sealing member (166) being configured to conform to a portion of the air conditioning assembly (118) disposed within the opening (122).

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