Blade assembly for distribution of stratified fluids in an aircraft
阅读说明:本技术 用于飞机中分层流体的分布的叶片组件 (Blade assembly for distribution of stratified fluids in an aircraft ) 是由 布鲁诺·弗莱彻 G·奥利维拉 乔恩·库里 约翰·比尔斯塔克 奥列克山大·瓦瑞柴夫 于 2019-07-30 设计创作,主要内容包括:本文教导一种用于飞机中分层流体的分布的叶片组件。叶片组件包括壳体,壳体包括壳体入口和壳体出口。壳体入口构造成接收分层流体,其中分层流体包括第一部分和第二部分。壳体出口构造成排出分层流体。壳体在壳体入口和壳体出口之间限定内部壳体容积。叶片组件还包括叶片,叶片设置在内部壳体容积内并将内部壳体容积一分为二。叶片包括邻近壳体入口的前缘和邻近壳体出口的后缘。后缘从前缘成角度地偏移。(A blade assembly for distribution of stratified fluid in an aircraft is taught herein. The blade assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive a stratified fluid, wherein the stratified fluid includes a first portion and a second portion. The housing outlet is configured to discharge the stratified fluid. The housing defines an internal housing volume between a housing inlet and a housing outlet. The blade assembly also includes a blade disposed within and bisecting the inner shell volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge.)
1. A blade assembly for distribution of a stratified fluid in an aircraft, the stratified fluid including a first portion and a second portion, the blade assembly comprising:
a housing comprising a housing inlet configured to receive the stratified fluid and a housing outlet spaced apart from the housing inlet and configured to discharge the stratified fluid, and the housing defining an internal housing volume between the housing inlet and the housing outlet; and
a vane disposed within and bisecting the interior shell volume, the vane including a leading edge adjacent the shell inlet and a trailing edge adjacent the shell outlet, the vane having a first side and a second side opposite the first side, the first and second sides extending between the leading and trailing edges, and the trailing edge being angularly offset from the leading edge relative to the first and second sides;
wherein the first side is configured to direct the first portion between the housing inlet and the housing outlet, and the second side is configured to direct the second portion between the housing inlet and the housing outlet.
2. The blade assembly of claim 1, wherein a leading edge of the blade defines a plane extending from the leading edge to the trailing edge, and the trailing edge is angularly offset from the leading edge relative to the plane by an amount of at least about +/-10 degrees.
3. The blade assembly of claim 1, wherein the blade has a substantially helical configuration extending from a leading edge of the blade to a trailing edge of the blade.
4. The blade assembly of claim 1, wherein the leading edge has a substantially linear configuration.
5. The blade assembly according to claim 1, wherein the trailing edge has a generally U-shaped configuration defining a recess.
6. The blade assembly of claim 1, wherein the shell has a substantially cylindrical configuration.
7. The blade assembly of claim 1, wherein the stratified fluid comprises a stratified air flow, and a first portion of the stratified air flow and a second portion of the stratified air flow have a temperature difference in an amount of at least 5 ℃.
8. A conduit for distribution of a stratified fluid in an aircraft, the stratified fluid comprising a first portion and a second portion, the conduit comprising:
an upstream portion configured to receive the stratified fluid;
a downstream portion spaced apart from the upstream portion and configured to discharge the stratified fluid;
an inner surface disposed between the upstream portion and the downstream portion, and the inner surface defining an interior conduit volume between the upstream portion and the downstream portion; and
a vane disposed within and bisecting the interior conduit volume, the vane including a leading edge adjacent the upstream portion and a trailing edge adjacent the downstream portion, the vane having a first side and a second side opposite the first side, the first and second sides extending between the leading and trailing edges, and the trailing edge being angularly offset from the leading edge relative to the first and second sides;
wherein the first side is configured to direct the first portion between the upstream portion and the downstream portion, and the second side is configured to direct the second portion between the upstream portion and the downstream portion.
9. The duct of claim 8, wherein the duct further comprises a first duct outlet and a second duct outlet, the first duct outlet and the second duct outlet in fluid communication with a downstream portion of the duct, the second side of the vane adjacent the trailing edge facing the first duct outlet, and the first side of the vane adjacent the trailing edge facing the second duct outlet.
10. The duct of claim 9, wherein a first side of the vane is configured to receive a first portion of the stratified fluid and discharge the first portion to the second duct outlet, and a second side of the vane is configured to receive a second portion of the stratified fluid and discharge the second portion to the first duct outlet.
11. The duct of claim 8, wherein the duct further comprises a vane assembly disposed within the inner duct volume, the vane assembly comprising a housing and the vane, the housing comprising a housing inlet configured to receive the stratified fluid and a housing outlet spaced apart from the housing inlet and configured to discharge the stratified fluid, the housing defining an inner housing volume between the housing inlet and the housing outlet, and wherein the vane is disposed within the inner housing volume and bisects the inner housing volume.
12. The duct of claim 11, wherein the housing has an outer surface opposite the inner housing volume and includes a shoulder extending around the outer surface.
13. The conduit of claim 12, wherein the conduit further comprises a locking ring configured to abut a shoulder of the housing, an inner surface of the conduit defines a groove adjacent the shoulder, and the groove is configured to receive the locking ring to minimize lateral movement of the blade assembly within the conduit.
14. The conduit of claim 12, wherein the conduit further comprises a pin extending into the internal housing volume, the shoulder of the housing defines a notch, and the notch is configured to receive the pin to minimize rotational movement of the blade assembly within the conduit.
15. The duct of claim 8, wherein the duct includes a sleeve configured to support the vane assembly, the sleeve disposed between and coupled to an upstream portion of the duct and a downstream portion of the duct for coupling the upstream and downstream portions together.
16. An aircraft, comprising:
a pipe for distribution of a stratified fluid comprising a first portion and a second portion, the pipe comprising:
an upstream portion configured to receive a stratified fluid;
a downstream portion spaced apart from the upstream portion and configured to discharge the stratified fluid;
an inner surface disposed between the upstream portion and the downstream portion, and the inner surface defining an interior conduit volume between the upstream portion and the downstream portion; and
a vane assembly disposed within the inner duct volume, the vane assembly comprising:
a housing comprising a housing inlet configured to receive the stratified fluid and a housing outlet spaced apart from the housing inlet and configured to discharge the stratified fluid, and defining an internal housing volume between the housing inlet and the housing outlet, an
A vane disposed within and bisecting the interior shell volume, the vane including a leading edge adjacent the shell inlet and a trailing edge adjacent the shell outlet, the vane having a first side and a second side opposite the first side, the first and second sides extending between the leading and trailing edges, and the trailing edge being angularly offset from the leading edge relative to the first and second sides,
wherein the first side is configured to direct the first portion between the housing inlet and the housing outlet, and the second side is configured to direct the second portion between the housing inlet and the housing outlet.
17. The aircraft of claim 16, wherein the duct further comprises a first duct outlet and a second duct outlet, the first duct outlet and the second duct outlet in fluid communication with a downstream portion of the duct, the second side of the blade adjacent the trailing edge facing the first duct outlet, and the first side of the blade adjacent the trailing edge facing the second duct outlet.
18. The aircraft of claim 17, further comprising a precooler, wherein the precooler is in fluid communication with an upstream portion of the duct and is configured to produce the stratified fluid, the first side of the vane is configured to receive a first portion of the stratified fluid and discharge the first portion to the second duct outlet, and the second side of the vane is configured to receive a second portion of the stratified fluid and discharge the second portion to the first duct outlet.
19. The aircraft of claim 17, further comprising a wing anti-icing system in fluid communication with the first duct outlet and an environmental control system in fluid communication with the second duct outlet.
20. The aircraft of claim 16, wherein the stratified fluid comprises a stratified air flow, and the first portion of the stratified air flow and the second portion of the stratified air flow have a temperature differential of at least 5 ℃, and wherein the duct and the housing comprise materials configured to withstand the temperature differential without significant deformation.
Technical Field
The present disclosure relates generally to vehicles and, more particularly, to the distribution of stratified fluids in aircraft.
Background
Aircraft typically employ Environmental Control Systems (ECS) to pressurize the passenger cabin of the aircraft and/or thermal anti-icing systems to provide heated air for anti-icing applications, such as wing anti-icing (WAI) systems. The air supply to these systems is typically provided by bleed air (bleed air) extracted or provided from the compressor and engine bypass of the aircraft engine. In order to meet the pressure and/or temperature requirements of various aircraft systems, hot bleed air is typically extracted from the high or low stage of the aircraft engines, while cold air is bypassed from the aircraft engines.
Mixing the low and high stage bleed air streams to a desired set temperature, thereby obtaining a heat exchanger called a precooler; the mixed stream is at an elevated temperature. At the precooler, the hot mixed bleed air stream is cooled by fan air consumed from the engine bypass duct. The cooled resultant pilot stream is then directed from the precooler through a single conduit for distribution to the WAI system and the ECS. The bleed air stream exiting the precooler is subject to large temperature stratification (i.e., large cold/hot temperature variations) that, if left unmanaged, can have a significant impact on the WAI system and ECS performance. For example, if the higher temperature portion of the bleed air flow from the precooler is directed to the ECS and the lower temperature portion of the bleed air flow from the precooler is directed to the WAI systems, these systems will not operate efficiently.
Accordingly, it is desirable to provide improved distribution of stratified fluids, such as stratified air streams. Furthermore, other desirable features and characteristics will become apparent from the subsequent summary and the detailed description, and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background.
Disclosure of Invention
Various non-limiting embodiments of a blade assembly for distribution of a stratified fluid in an aircraft, a conduit for distribution of a stratified fluid in an aircraft, and an aircraft including a conduit for distribution of a stratified fluid are disclosed herein.
In one non-limiting embodiment, the blade assembly includes, but is not limited to, a housing. The housing includes, but is not limited to, a housing inlet and a housing outlet. The housing inlet is configured to receive a stratified fluid. The layered fluid includes, but is not limited to, a first portion and a second portion. The housing outlet is spaced from the housing inlet. The housing outlet is configured to discharge the stratified fluid. The housing defines an internal housing volume between the housing inlet and the housing outlet. The blade assembly also includes, but is not limited to, a blade disposed within and bisecting the internal shell volume. The vanes include, but are not limited to, a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The blade has a first side and a second side opposite the first side. The first and second sides extend between the leading and trailing edges. The trailing edge is angularly offset from the leading edge relative to the first and second sides. The first side is configured to direct the first portion between the housing inlet and the housing outlet, and the second side is configured to direct the second portion between the housing inlet and the housing outlet.
In another non-limiting embodiment, the conduit includes, but is not limited to, an upstream portion configured to receive the stratified fluid. The layered fluid includes a first portion and a second portion. The conduit also includes, but is not limited to, a downstream portion spaced apart from the upstream portion and configured to discharge the stratified fluid. The conduit also includes, but is not limited to, an inner surface disposed between the upstream portion and the downstream portion. The inner surface defines an interior conduit volume between the upstream portion and the downstream portion. The duct also includes, but is not limited to, vanes disposed within and bisecting the interior duct volume. The blade includes a leading edge adjacent the upstream portion and a trailing edge adjacent the downstream portion. The blade has a first side and a second side opposite the first side. The first and second sides extend between the leading and trailing edges. The trailing edge is angularly offset from the leading edge relative to the first and second sides. The first side is configured to guide the first portion between the upstream portion and the downstream portion, and the second side is configured to guide the second portion between the upstream portion and the downstream portion.
In another non-limiting embodiment, the conduit includes, but is not limited to, an upstream portion configured to receive the stratified fluid. The layered fluid includes a first portion and a second portion. The conduit also includes, but is not limited to, a downstream portion spaced apart from the upstream portion and configured to discharge the stratified fluid. The conduit also includes, but is not limited to, an inner surface disposed between the upstream portion and the downstream portion. The inner surface defines an interior conduit volume between the upstream portion and the downstream portion. The duct also includes, but is not limited to, a vane assembly disposed within the internal duct volume. The blade assembly includes, but is not limited to, a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid. The housing outlet is spaced apart from the housing inlet and is configured to discharge the stratified fluid. The housing defines an internal housing volume between the housing inlet and the housing outlet. The blade assembly also includes, but is not limited to, a blade disposed within and bisecting the internal shell volume. The vanes include, but are not limited to, a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The blade has a first side and a second side opposite the first side. The first and second sides extend between the leading and trailing edges. The trailing edge is angularly offset from the leading edge relative to the first and second sides. The first side is configured to direct the first portion between the housing inlet and the housing outlet, and the second side is configured to direct the second portion between the housing inlet and the housing outlet.
Drawings
The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, an
FIG. 1 is a perspective view of a non-limiting embodiment of a blade assembly for distribution of stratified fluids in an aircraft;
FIG. 2 is another perspective view illustrating the blade assembly of FIG. 1;
FIG. 3 is a cross-sectional perspective view showing the blade assembly of FIG. 1;
FIG. 4 is a partially transparent perspective view illustrating a conduit for distribution of a stratified fluid in an aircraft;
FIG. 5 is a cross-sectional perspective view illustrating a duct including the locking ring and blade assembly of FIG. 1;
FIG. 6 is a cross-sectional perspective view illustrating a duct including the pin and blade assembly of FIG. 1;
FIG. 7 is an exploded view illustrating the duct of FIG. 4 including the blade assembly of FIG. 1;
FIG. 8 is a partially transparent perspective view illustrating an aircraft including the conduit for distribution of stratified fluid of FIG. 4;
FIG. 9 is a schematic illustration showing the aircraft of FIG. 8; and
10A, 10B, and 10C are schematic diagrams illustrating the duct of FIG. 4 including the blade assembly of FIG. 1 arranged in three different orientations.
Detailed Description
The following detailed description is merely exemplary in nature and is not intended to limit the systems and methods as described herein. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description.
In exemplary embodiments, conduits for distribution of stratified fluids in an aircraft are taught herein. The conduit includes an upstream portion configured to receive the stratified fluid from the precooler. The layered fluid includes a first portion and a second portion different from the first portion. The first portion of the stratified fluid and the second portion of the stratified fluid have a temperature difference in an amount of at least about 5 ℃. The duct also includes a downstream portion spaced apart from the upstream portion and configured to discharge the stratified fluid through a first duct outlet to a wing anti-icing (WAI) system and through a second duct outlet to an Environmental Control System (ECS).
The duct also includes a vane assembly disposed within the duct. The blade assembly includes a housing. The housing includes a housing inlet and a housing outlet. The blade assembly further includes a blade. The blades are disposed within the housing. The vanes divide the inner housing volume in two. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The blade has a first side extending between the leading edge and the trailing edge and a second side opposite the first side. The trailing edge is angularly offset relative to the first and second sides by an amount of at least about +/-135 degrees from the leading edge such that the blade may have a substantially helical configuration extending from the leading edge to the trailing edge. The first side of the vane is configured to direct a first portion of the stratified fluid between the housing inlet and the housing outlet. Further, the second side of the vane is configured to direct a second portion of the stratified fluid between the housing inlet and the housing outlet.
The first part of the stratified fluid produced by the precooler has a lower temperature and the second part of the stratified fluid produced by the precooler has a higher temperature. The first side of the vane may be configured to receive a first portion of the stratified fluid and discharge the first portion to the second conduit outlet. The ECS may then receive the first portion from the second conduit outlet. Likewise, the second side of the vane is configured to receive a second portion of the stratified fluid and discharge the second portion to the first conduit outlet. The WAI system may then receive the second portion from the first conduit outlet. In this way, the blade assembly improves the distribution of stratified fluid to the components of the aircraft, i.e., the WAI system and the ECS, thereby increasing the efficiency of the ECS and the WAI system. Without the blade assembly, the second portion (higher temperature) would be discharged through the second conduit outlet to the ECS and the first portion (lower temperature) would be discharged through the first conduit outlet to the WAI system, potentially adversely affecting the efficiency of the ECS and WAI systems.
A better understanding of the above-described system may be obtained through a review of the figures and the following detailed description of the present application.
Fig. 1 and 2 are perspective views illustrating a non-limiting embodiment of a
With reference to fig. 7 and with continuing reference to fig. 1 and 2, in various embodiments, the stratified fluid comprises a stratified air flow. In these embodiments, the stratified air flow includes a
With continued reference to fig. 1 and 2, the
Fig. 3 is a sectional perspective view illustrating the
With continued reference to fig. 1, 2, and 3, the
With continued reference to fig. 1, 2, 3, and 7, the
Fig. 4 is a partially transparent perspective view illustrating a
As described above, the
In certain embodiments, the
In various embodiments, the
FIG. 5 is a cutaway perspective view illustrating the
FIG. 6 is a cross-sectional perspective view illustrating the
FIG. 7 is an exploded view illustrating the
Fig. 8 is a partially transparent perspective view illustrating the
Fig. 9 is a schematic diagram illustrating the
In the exemplary embodiment,
In various embodiments, the
10A, 10B, and 10C are schematic diagrams illustrating the
While at least one exemplary embodiment has been presented in the foregoing detailed description of the disclosure, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the disclosure as set forth in the appended claims.