Abstract:
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application is a continuation of U.S. patent application Ser. No. 11/196,508, filed on Aug. 4, 2005, now U.S. Pat. No. 7,364,117 which is a continuation of U.S. patent application Ser. No. 10/608,224, filed on Jun. 30, 2003, now U.S. Pat. No. 6,942,181, which is a continuation of U.S. patent application Ser. No. 10/020,363 filed Oct. 29, 2001, now issued as U.S. Pat. No. 6,651,929, the entire contents of each of which are incorporated herein by reference. 
    
    
     TECHNICAL FIELD 
     The present invention relates to cooling systems for auxiliary power units on airplanes and, more particularly, pertains to the passive cooling of the components and oil of such units and the enclosure ventilation of such units. 
     BACKGROUND OF THE INVENTION 
     Large aircraft often use an on-board auxiliary power unit (APU) to provide electrical power and compressed air for systems throughout the airplane. When the aircraft is grounded, the APU provides the main source of power for environmental control systems, hydraulic pumps, electrical systems and main engine starters. During flight, the APU can supply pneumatic and electric power. 
     Auxiliary power units are generally small gas turbine engines, often mounted in the aft tail section of the aircraft. They require a certain amount of cooling air, and are lubricated by oil that is generally cooled by an oil cooler which also requires cooling air. Active cooling systems are usually employed to provide this cooling air, and are typically comprised of an active fan used to push air through the oil cooler and across auxiliary power unit components. These fans are driven at high speeds by the APU through a complex shaft and gear assembly. The mechanical complexity and high operating speeds of these fans increases the possibility of failure. Active fan cooling systems therefore can significantly reduce the reliability of an auxiliary power unit. 
     While APU passive cooling systems which eliminate the need for active fan cooling systems are well known, they all generally draw cooling air into the APU compartment, before it is drawn through the air cooled oil cooler. This arrangement causes the cooling air to be heated up in the compartment before it reaches the oil cooler, and therefore, oil cooling is not optimized. U.S. Pat. No. 5,265,408, for example, discloses a method and apparatus for cooling a compartment mounted gas turbine engine comprising a first exhaust eductor within which is mounted an oil cooler, and which incorporates a mixer nozzle to entrain cooling air flow first through the APU compartment and then through the oil cooler. Surge bleed flow from the load compressor is discharged into the exhaust eductor. Ambient air is received into the compartment through a second exterior eductor inlet. 
     U.S. Pat. No. 5,655,359 similarly discloses an APU passive cooling system wherein cooling air for the oil cooler is drawn from the compartment. An inlet scoop in the engine air intake duct used to divert a portion of the air flow into the APU compartment. This air is used to cool the engine before being drawn through the oil cooler, mounted in a vacuum duct, by a lobed mixer which acts as an aspirator. 
     U.S. Pat. No. 6,092,360 discloses an APU passive cooling system in which cooling air is drawn into the engine compartment through an opening located in the rear of the aircraft. An eductor mounted before the exhaust duct of the engine, draws compartment air through the oil cooler, which in turn draws atmospheric air in through the aft opening. 
     Thus, while these patents provide for cooling of an auxiliary power unit without the use of a mechanically driven fan, they all teach systems which draw cooling air for the oil cooler from the APU compartment. A need exists for an auxiliary power unit passive cooling system that can provide enhanced oil cooling capabilities by directing exterior cooling air, through ducts, directly to the oil cooler, and which is nevertheless adaptable enough to be able to provide damage protection from foreign objects and be combined with the engine compressor surge bleed flow to provide improved airflow through the oil cooling heat exchanger. 
     SUMMARY OF THE INVENTION 
     It is an object of the present invention to provide an improved cooling system for an auxiliary power unit on an airplane. 
     It is also an object of the present invention to provide a simpler cooling system for auxiliary power unit engine oil and external components which does not require moving parts and does not include a cooling fan. 
     It is a further object of the present invention to provide improved cooling of the oil in an auxiliary power unit by providing enhanced cooling airflow through the heat exchanger. 
     Therefore, in accordance with the present invention there is provided a passive cooling system for an auxiliary power unit installation on an aircraft, comprising an auxiliary power unit housed within a nacelle of the aircraft, the auxiliary power unit comprising at least a compressor portion of a gas turbine engine and an oil cooler contained separately within the nacelle, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first cooling air inlet duct communicating with a second opening defined in the nacelle and with the compressor portion, the oil cooler located within a second duct communicating with the exterior of the nacelle and the engine exhaust opening whereby exterior cooling air, and engine exhaust ejected through the engine exhaust opening entrains cooling air through the second duct to the oil cooler, providing engine oil cooling. 
     In accordance with the present invention, there is also provided a passive cooling system for an auxiliary power unit installation on an aircraft, comprising: an auxiliary power unit housed within a nacelle of the aircraft, the auxiliary power unit comprising at least a compressor portion of a gas turbine engine and an oil cooler contained separately within said nacelle; an engine exhaust opening defined in the aft portion of said nacelle and communicating with said gas turbine engine via an exhaust eductor assembly; said exhaust eductor assembly being in fluid flow communication with a compressor surge bleed duct; at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion; and said oil cooler located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with said engine exhaust opening, whereby exterior cooling air and engine exhaust ejected through said exhaust eductor assembly, entrain cooling air through said second duct to said oil cooler, providing engine oil cooling. 
     In accordance with a more specific embodiment of the present invention, the engine air inlet includes a first duct portion, and the second duct is bifurcated from the first duct portion and extends downstream from the first duct portion with a third duct portion also formed downstream of the first duct, the third duct portion communicating with the compressor portion and the oil cooler located within the second duct portion providing direct exterior cooling air to the oil cooler. 
     In one embodiment, contamination of aircraft environmental control system air is prevented by an air inlet splitter, which isolates the load compressor gas path. Protection against damage from foreign objects, for the powerplant, may be provided by a bypass duct located in-line with the first air inlet duct, and a scavenger discharge duct and outlet which expels harmful foreign objects from the aircraft. The nacelle is provided with a rear exhaust opening, and at least a second opening for the outside air intake. The third air inlet duct portion directs the air from the air intake to the engine compressor portion. The auxiliary power unit comprises a gas turbine engine having both load and core compressors and a compressor surge bleed valve and duct. The oil cooler may comprise an air-to-oil heat exchanger. The engine exhaust ejector creates a depressurization in the nacelle or in the exhaust eductor assembly, which results in the entrainment of cooling air through the heat exchanger and through the nacelle. In at least one embodiment, a dedicated small opening in the exhaust eductor assembly permits nacelle ventilation. 
     Further features and advantages of the present invention will become fully apparent by referring to the following detailed description, claims, and the appended drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a cross sectional schematic illustration of a first embodiment of the APU passive cooling system in accordance with the present invention. 
         FIG. 2 a    is a cross sectional schematic illustration of a second embodiment of the APU passive cooling system in accordance with the present invention. 
         FIG. 2 b    is a cross sectional schematic illustration of the second embodiment of the APU passive cooling system shown in  FIG. 2   a.    
         FIG. 3  is a cross sectional schematic illustration of a third embodiment of the APU passive cooling system in accordance with the present invention. 
         FIGS. 4 a  to 4 d    are cross sectional schematic illustrations of a fourth embodiment of the APU passive cooling system in accordance with the present invention. 
         FIG. 5  is a perspective view of an engine having a main air inlet duct and exhaust eductor assembly in accordance with the present invention. 
         FIG. 6  is a vertical cross-sectional view of an exhaust eductor assembly used in accordance with the present invention. 
         FIG. 7  is a perspective view of the cooling air flow inner shroud of the exhaust eductor assembly shown in  FIG. 6 . 
         FIG. 8  is a side perspective view of the exhaust eductor assembly shown in  FIG. 6 . 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     Referring to the drawings,  FIG. 1  embodies an APU installation  10  comprising the elements of the present invention that will be described. The APU installation  10  is principally comprised of a gas turbine power plant  12  and an oil cooler  14 , both within an auxiliary power unit nacelle  16 . This nacelle is defined for the purposes of the present invention, as any dedicated enclosed compartment or enclosure, generally although not essentially located within the aircraft tailcone. The nacelle  16  shown in these embodiments as an aft compartment in the aircraft, has an exterior skin surface  18 . Compartment access doors  42  allow external access to the auxiliary power unit when the aircraft is on the ground, for such purposes as engine maintenance. 
     In the embodiment shown in  FIG. 1 , the exterior surface  18  of the APU nacelle  16  comprises principally two openings, the rear exhaust opening  20  and the main air inlet opening  22 . The main air inlet opening  22  in the aircraft exterior skin  18  allows air to be drawn from outside the aircraft by the power plant compressors. The gas turbine engine power plant  12  is comprised of two compressors, a load compressor  34  and a core compressor  36 . The load compressor  34  provides the aircraft environmental control system (ECS) air, while the core compressor  36  provides the powerplant with air for combustion. Inlet air is directed by a first air inlet duct  24  from the air inlet opening  22  to the power plant compressors. The oil cooler  14 , shown to be normal to the direction of airflow but is not necessarily limited to this orientation, is located in a second duct  27 . A bifurcation  26  in the first air inlet duct  24  is provided to directly supply cooling air to the oil cooler  14 , in the form of an air-to-oil heat exchanger, through the second duct  27 . This allows air to be directly fed to the oil cooler  14  through a duct, providing improved cooling airflow. After passing through the oil cooler, the cooling air enters the APU compartment  16  to provide cooling to the APU components. 
     An exhaust ejector  38  of the powerplant  12 , causes a depressurization of the APU compartment  16 . The exhaust ejector  38  achieves this by reducing the diameter of the power plant exhaust passage, causing an increase in the velocity of the exhaust gases. This causes the depressurization upstream in the APU compartment  16 , resulting in entrainment of the cooling air through the heat exchanger and the APU compartment, thereby cooling the engine oil and the powerplant components within the APU compartment. 
     Within the first air inlet duct  24  is located an air inlet splitter  28 . The splitter  28  in the engine air inlet duct  24  extends down into the engine intake plenum  30 . The air splitter  28  and the bifurcation  26  in the first air inlet duct are positioned such that the bifurcation  26  in the inlet duct is downstream of the leading edge  32  of the splitter  28 . When the power plant is run with the access doors  42  open, the resulting ambient pressure in the APU compartment  16  equalizes with the outside air pressure, which causes a flow reversal within the heat exchanger as the power plant creates a depression within the first air inlet duct  24 . In this operating mode, a reversal of airflow occurs, as the air is entrained from the compartment, through the heat exchanger and the second duct  27 , and gets ingested into the engine. The splitter  28 , consequently, prevents contamination of the airflow of the load compressor  34  in the event of a leak in the heat exchanger  14  when the powerplant is operated with the compartment access doors  42  open. Therefore, any oil leaked from the heat exchanger is forced down the core compressor and burned by the engine, rather than contaminating the aircraft environmental control system air. 
       FIGS. 2 a  and 2 b    illustrate an alternate embodiment of the passive cooling system. Referring to the embodiment illustrated in  FIG. 2 a   , a heat exchanger air inlet duct  59  directs cooling air from a bifurcation  58  in the main engine air inlet duct  24  to the heat exchanger  14 , and a heat exchanger discharge duct  52  directs cooling air downstream of the heat exchanger  14  directly to an exhaust eductor assembly  57 . The exhaust eductor, or exhaust ejector plenum, while it is generally an annular plenum adapted to receive exiting APU cooling air which is drawn through the eductor and into the engine exhaust by the depressurization caused by the engine exhaust ejector  38 , could alternately be any similar device of varying shape which performs the equivalent function. APU component cooling air is admitted into the APU compartment through a small second bifurcation  54  in the heat exchanger air inlet duct  59 . The component cooling air then exits the APU compartment  16  through another small bifurcation  56  in the exhaust eductor assembly  57 . The surge bleed duct  48  is combined with the heat exchanger discharge duct  52  downstream of both the surge bleed valve  50  and the heat exchanger  14 . The mixing plane for the mixing of heat exchange airflow and exhaust flow is shown as  520 . This combined heat exchanger and surge bleed duct design, while preventing contaminating oil from the heat exchanger  14  from entering the aircraft bleed system or the ECS air, provides further enhanced airflow through the heat exchanger when the surge bleed valve  50  is open. 
     In the embodiments shown in  FIGS. 2 a  and 2 b   , the oil cooler is located further forward with respect to the engine, nearer the gearbox casing of the power plant and close to the oil pumps of the engine. This eliminates the need for long oil lines. The surge bleed valve  50  is closed when the APU supplies bleed air to the aircraft. However, when the APU only supplies electric power, the surge bleed valve  50  is opened, and the junction between the surge bleed duct  48  and the heat exchanger discharge duct  52  is designed to enhance air flow through the heat exchanger using the additional kinetic energy of the surge bleed flow, thereby improving oil cooling. As in the embodiment of  FIG. 1 , the exhaust ejector  38 , here within the exhaust eductor assembly  57 , causes the entrainment of cooling air flow through the heat exchanger and out through the engine exhaust duct  110 . 
       FIG. 2 b    illustrates a similar embodiment as  FIG. 2 a   , having, however, a dedicated heat exchanger opening  44  in the exterior surface  18  of the nacelle compartment  16 . This provides outside air via the alternate heat exchanger inlet duct  46  to the heat exchanger  14 . In this embodiment, the compartment cooling air inlet  54  is shown to be located in the first air inlet duct  24  rather than the heat exchanger inlet duct  59 . Nevertheless, either location for the compartment air inlet  54  is possible. The embodiment shown in  FIG. 2 b   , however, provides independent air cooling sources for the oil cooler and the engine components within the APU compartment. The advantage of this embodiment over that shown in  FIG. 1  is that more efficient cooling of the engine components is achieved because cooling air does not first get warmed by first going through the heat exchanger before it reaches the APU components. 
       FIG. 3  shows a further embodiment of the present invention. This embodiment additionally includes a duct providing foreign object damage protection for the engine. The power plant compressors draw air from the outside through a main air inlet opening  22  in the aircraft skin exterior surface  18 . The engine air inlet duct  24  directs the air to the engine compressors. According to the embodiment shown in  FIG. 2 b   , a small bifurcation  54  in the inlet duct is provided to supply cooling air to the APU compartment. The exhaust ejector  38  within the exhaust eductor assembly  57  creates a depressurization of the APU compartment resulting in airflow through the bifurcation opening  54  in the air inlet duct. Cooling air exits the APU compartment through a second bifurcation  56  in the exhaust eductor assembly  57 . 
     An in-line bypass duct  60  is adjoined to the first air inlet duct  24 , in order to direct cooling air to the heat exchanger  14 , located in the mouth of the eductor assembly  57  parallel to the direction of airflow in the bypass duct. The airflow in the bypass duct  60  is sustained by the eductor induced flow through the oil cooling heat exchanger. One advantage this embodiment permits is the use of a smaller oil cooler. A scavenge discharge duct  62  is used as a collector to discharge overboard any foreign objects collected by the bypass duct  60 . The bypass and scavenge ducts are designed such that separated liquid and solid particles will drain or be drawn by gravity out through the scavenge duct exit  64 . The scavenge duct  62  and scavenge exit  64  are sized such that flow reversal is minimized during aircraft static and low speed conditions which cause flow reversal in the scavenge duct. The air bypass and the scavenge ducts  60  and  64  respectively, provide a level of foreign object damage protection for the powerplant. 
       FIGS. 4 a  to 4 d    show another embodiment of the present invention wherein the oil cooler  14  is located within the exhaust eductor assembly  57  and the dedicated heat exchanger inlet duct  46  feeds air directly from the aircraft exterior to the oil cooler. Dedicated heat exchanger opening  44  in the exterior surface  18  of the aircraft&#39;s nacelle compartment  16  permits exterior air to be fed through the inlet duct  46  to the oil cooler  14  located perpendicular to the inlet air flow in the annular exhaust eductor assembly  57 . The engine exhaust ejector  38  within the eductor assembly  57  draws the cooling air through the heat exchanger inlet duct  46  and the oil cooler  14 , and out into the main engine exhaust duct  40 . As can be seen in  FIG. 4 a   , the surge bleed air flowing through duct  48  is injected into one of the heat exchange air flow and the gas turbine exhaust flow upstream of the plane  39  where these two flows mixed together. 
     The variations of the fourth embodiment of the present invention shown in  FIGS. 4 a  to 4 d   , involve alternate locations of the compartment cooling air inlet and exits.  FIG. 4 a    shows an embodiment wherein the compartment cooling air inlet  54  is a bifurcation in the main engine air inlet duct  24 . This permits air to enter the nacelle compartment  16  to provide cooling to the externals of the APU. This cooling air then exits the compartment through a bifurcation in the heat exchanger inlet duct  46  for the compartment cooling air exit  68 . The embodiment shown in  FIG. 4 b    uses a compartment cooling air inlet  70  in the heat exchanger inlet duct  46 . The compartment cooling air then exits the nacelle compartment through a small bifurcation  56  in the exhaust eductor assembly  57 , similar to the embodiments of  FIGS. 2 and 3 . The embodiments of  FIGS. 4 c  and 4 d    both have a separate compartment cooling air inlet  72  in the exterior surface  18  of the nacelle compartment  16 . The engine exhaust ejector  38  pulls cooling air from the exterior of the aircraft via the air inlet  72 , through the compartment  16 , and out through either the air exit bifurcation  56  in the exhaust eductor  57 , as shown in  FIG. 4 c   , or the air exit bifurcation  68  in the heat exchanger inlet duct  46 , as shown in  FIG. 4   d.    
       FIG. 5  shows an embodiment of the APU installation  10 , comprising the gas turbine power plant  12 , the oil cooler  14  and the exhaust eductor assembly  57 . 
     The assembly shown in  FIG. 6  consists of a construction of sheet metal components either welded or riveted together. The assembly is of modular design and is supported by the engine exhaust casing  81 . The exhaust eductor assembly comprises a primary nozzle  82  located immediately downstream of the engine exhaust gas path. The gas path of the primary nozzle  82  is bounded by the primary nozzle shroud  83  and exhaust plug  84 . The primary nozzle is circumscribed by the surge bleed nozzle  85 , which is bounded by the cooling air plenum inner shroud  86  and the primary nozzle shroud  83 . The conical cooling air mixing plane is located downstream of the primary nozzle  82 . 
     Mixing lobes  87  are introduced in a lobed mixer  112  to improve the mixing efficiency, thereby resulting in improved cooling mass flow. The number of lobes within the eductor assembly inner shroud may vary depending on exhaust duct diameter and cooling air flow requirements. Similarly, the geometrical shape of the mixing lobes  87  may vary based on pumping requirements and acoustics. These mixing lobes  87  can be either welded or mechanically fastened to the cooling air plenum inner shroud  86 . 
     The eductor assembly incorporates a primary surge bleed plenum  88  in which the surge bleed flow is redistributed circumferentially before exiting through a series of openings on the surge bleed flow plenum inner shroud  89  and entering the secondary surge bleed plenum  90 . In this plenum, the surge bleed flow is realigned axially and then ejected back into the main engine gas path through the surge bleed nozzle  85 . The primary surge bleed plenum  88  is fed, during specific engine operating conditions, by the surge bleed duct  48 . This surge bleed flow is controlled by the modulating surge bleed valve  50  located in the surge bleed duct  48 . Flow from the surge bleed duct  48  enters the primary surge bleed plenum  88 , at the junction  93  of the two components, in a radial direction and impinges directly on the diaphragm  94 , which divides the primary surge bleed plenum  86  and the cooling air plenum  95 . This diaphragm  94  has a conical shape and acts as a natural splitter to redistribute the surge bleed flow uniformly around the circumference of the surge bleed plenum inner shroud  89 . 
     The cooling air plenum  95  located on the aft side of the diaphragm  94  is bounded by the cooling air plenum outer shroud  96  and inner shroud  86 . Openings  97  are provided on the outer shroud for the cooling air to enter the cooling air plenum  95 . The air cooled heat exchanger  14  is located upstream of these openings. Both the surge bleed flow and the cooling air flow plenums  88  and  95  respectively are sealed to prevent any leakage. 
     A mechanical interface  98  is provided on the downstream end of the eductor assembly for connecting to the aircraft exhaust duct  40 . Opening  56  is provided on the cooling air plenum outer shroud in order to accept ventilation air exiting from the engine compartment. The cutouts  80  on the cooling air flow inner shroud  86 , as seen in  FIG. 7 , are provided in line with each mixing lobe  87 . 
     The layout of the eductor assembly as described in detail above offers several additional advantages. The engine exhaust velocity can be easily altered by changing a simple axisymmetric part, namely, the primary nozzle shroud  83 , in order to improve the amount of secondary air flow used for cooling purposes. This can be easily done without requiring modification of any of the more complex and more expensive parts of the eductor assembly. Also, a large exhaust plug  84  is required in order to control the air flow in the primary nozzle  82  and the air flow into the primary passages of the mixing lobes  87 . The resulting large volume of space inside the exhaust plug  84  can then be used for acoustic treatment, for example, by introducing inside the plug low frequency cavities extending from the engine exhaust casing  81  interface to the cooling air flow mixing plane. 
     Therefore, in summary, the eductor assembly and passive cooling system of the present invention, provides engine oil cooling and engine enclosure cooling without requiring the use of any rotating parts and permits the reinjection of surge bleed flow into the main engine exhaust gas path thereby providing additional pumping capability to the cooling air. The eductor assembly is additionally capable of redistributing the surge bleed flow circumferentially within the surge bleed plenum, providing a method for controlling the pumping capability of the eductor assembly by the introduction of a simple axisymmetric primary nozzle shroud into the main exhaust gas path, and providing a method to control the noise generated by the engine in the eductor assembly by the introduction of a large exhaust plug with internal acoustic chambers. 
     The embodiments of the invention described above are intended to be exemplary only. The scope of the invention is therefore intended to be limited solely by the scope of the appended claims.