Abstract:
A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the event of a fire in the compartment. An associated means and method are also disclosed.

Description:
FIELD OF THE INVENTION 
   This invention relates generally cooling a gas turbine engine mounted in a compartment, and more particularly to apparatus and method for improving fire protection in such devices. 
   BACKGROUND 
   Auxiliary power unit nacelle compartments must be carefully ventilated to avoid “dead air” zones where flammable gases may undesirably collect and thus pose a potential fire threat. The compartment, however, despite the best efforts of designers does inevitably have zones where the ventilation is less than ideal, and thus fireproofing measures are not only desirable, but government regulations also require certain levels of fireproofing be present. Thus, for example, when a fire is detected in the compartment, typically a fire-suppressing liquid (such as halene) is dispensed into the compartment to control the flames. Fire resistant materials are also used in construction. For example, oil coolers in such systems are often constructed of stainless steel or the like, to provide fire protection should a fire occur in the compartment while the auxiliary power unit is in operation. The stainless steel provides better heat resistance (relative to generally preferred lighter-weight materials like aluminium, etc.) to the oil in the cooler in the presence of the high temperatures of a nearby fire. Such measures add weight to the overall design, however, and thus it would be desirable to provide improved, lighter weight measures for providing fire protection. 
   SUMMARY OF THE INVENTION 
   It is an object of this invention to provide an improved fire protection apparatus and method to an auxiliary power unit installation in an aircraft. 
   In a first aspect, the present invention provides a fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment, the oil cooler mounted to an exhaust eductor on an auxiliary power unit in the compartment, the oil cooler having a first side substantially facing the compartment and a second side mounted to the exhaust eductor, the fire protection apparatus comprising a fire shield mounted adjacent the oil cooler, the fire shield adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the event of a fire in the compartment. 
   In a second aspect, the present invention provides a fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment, the fire protection apparatus comprising shield means for blocking impingement of flames of a fire on the oil cooler. In a third aspect, the present invention provides a method of providing fire protection to an oil cooler mounted in an auxiliary power unit the compartment, the method comprising the steps of sensing a fire in the compartment and at least partially covering the oil cooler when a fire is sensed in the compartment to at least partially block flames from directly impinging on the oil cooler. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a schematic view of a typical passive cooling system for an auxiliary power unit according to the prior art. 
       FIG. 2  is an enlarged portion of the general system of  FIG. 1 , and incorporating a first embodiment of an apparatus according to the present invention. 
       FIG. 3  is an enlarged portion of the system of  FIG. 1 , and incorporating a second embodiment of an apparatus according to the present invention. 
       FIG. 4  is an enlarged portion of the system of  FIG. 1  (looking down on the air cooler), and incorporating a third embodiment of an apparatus according to the present invention. 
       FIG. 5  is an enlarged portion of the system of  FIG. 1 , and incorporating a fourth embodiment of an apparatus according to the present invention. 
   

   DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
     FIG. 1  schematically illustrates a prior art passive cooling system for an auxiliary power unit  10 . Auxiliary power unit  10  is positioned in a compartment  12 , which is located in the aft fuselage of an aircraft  14  having an exterior surface  16 . Compartment  12  is separated from the rest of the fuselage by a firewall  18 , and exterior surfaces  16  of aircraft  14  form the remaining walls of compartment  12 . Auxiliary power unit  10  typically includes a load compressor  20 , a power compressor  22  and a turbine  24 . An oil cooler  26  is provided to cool oil (not shown) used by auxiliary power unit  10 , as will be described further below. 
   An intake duct  30  extends between an intake opening  32  in exterior surface  16  and auxiliary power unit  10 . Intake duct  30  defines an airflow passage  34  through which auxiliary power unit  10  draws combustion air. Intake opening  32  permits air to flow in the direction of the arrows under the influence of auxiliary power unit  10  itself (ground operation) or the air stream of the aircraft and the auxiliary power unit (flight operation). Intake duct  30  also includes an inlet scoop  60  mounted therein to divert a portion of the air flowing through airflow passage  34  into compartment  12  via a compartment outlet  50 . Auxiliary power unit  10  also has an exhaust exit  70  positioned in an exhaust passage  74  leading to the exterior of aircraft  14 . An eductor  80  is positioned between exit  70  and oil cooler  26 . 
   When auxiliary power unit  10  is in operation, high-speed exhaust exiting at  70  creates a low-pressure region in eductor  80 . The low-pressure region in eductor  80  causes air to be drawn from compartment  12  and through oil cooler  26 , entering a compartment side  27  of the oil cooler  26  and then exiting from an eductor side  28  into eductor  80 . The cooling air is then mixed with the exhaust from auxiliary power unit  10  and expelled into the ambient environment. Oil passing through the oil cooler  26  is thus cooled by the air flow and kept within a desired operating temperature range. 
   To protect against the unlikely event of a fire breaking out in compartment  12 , all system components are provided with fire protection to prevent damage to the components, and to ensure a level of safety is maintained for the aircraft payload, ground service personnel, and the like. Since air is drawn from the compartment  12  into heat exchanger  26 , heat exchanger  26  must also be provided with fireproofing, and is thus typically stainless steel (or similar high-heat resistant material) to provide the desired level of fire protection. The additional weight added by the stainless steel components can be significant, however, relative to lighter-weight but less fire resistant materials such as aluminum which are typically preferred in non-fire-critical areas in aircraft construction). Therefore if aluminum is to be used, for example, it would be desirable to provide alternate fireproofing means for air cooler  26 . 
   Referring to  FIG. 2 , according to a first aspect of the present invention, a fire shield  90  is provided for selectively covering the heat exchanger in the event of a fire. An actuator member  100  is also provided to preferably automatically close fire shield  90  as soon as a fire is sensed in the compartment by an appropriate sensor(s) (not shown). The heat exchanger is preferably also clad with a fireproof material and insulation, as required. The oil cooler, thus protected in the event of a fire, may now be made of any material suitable for an oil cooler, such as aluminum. 
   In the embodiment of  FIG. 2 , fire shield  90  includes “cabinet” type doors  92  which are actively closed by an actuator  100  which is hydraulically actuated. The doors  92  are preferably steel doors of a sufficient thickness so as to be fireproof (e.g. 0.005″ thick or thicker is preferred, though any fireproof configuration will suffice). Two doors  92  are shown, but any number (including one) may be provided to substantially shield the cooler from a fire in the compartment. When closed, door(s)  92  protect the heat exchanger  26  from a compartment fire, and thereby allow the heat exchanger to be made of less fire-resistant material such as aluminum, which is of course beneficially lightweight. The weight savings on an typical commercial airliner auxiliary power unit installation could be upwards of 60 pounds, depending on the design and configuration. The benefit is therefore significant. 
   Fire shield  90  may also provide protection in a negative pressure scenario (air flowing backward through eductor into compartment) if the air cooler is sufficiently sealed by fire shield  90 . A further benefit is that, by cutting the airflow through the eductor in the event of a fire, door(s)  92  assist in dousing the fire in the compartment by impeding a diluting air flow into the compartment and thereby enhancing the concentration of halene (or other fire suppressant) in the compartment. 
   Fire shield  90  may have any suitable configuration which sufficiently blocks or otherwise shields the impingement of the flames of a compartment fire on exposed non-fireproof parts of the cooler  26 . Fire shield  90  may be mounted to oil cooler  26 , eductor  80  or another structure in compartment  12 . Preferably fire shield  90  protects the entirety of air cooler  26 , but it need not, depending on the particular circumstances of application. Fire shield  90  may also form part of a larger fire control apparatus provided for oil cooler  26  of the auxiliary power unit installation. 
   Referring to  FIG. 3 , in a second embodiment fire shield  90  includes a plurality or louvres  94  or blinds  94  mounted above oil cooler  26 . Blinds  94  are preferably actively closable by actuator member  100  in the event of a fire. Alternately, if properly placed and configured (as will be appreciated by one skilled in the art in light of this disclosure), louvres  94  may be unmovable or fixed, i.e. do not require to be closed in the event of a fire to provide adequate shielding to the oil cooler  94 . Rather, the lover slats are angled to provide shielding from direct impingement for flames from a compartment fire and yet still provide air access to the oil cooler in normal operation by way of a “tortuous” or other non-direct air path into the cooler  26 . 
   Referring to  FIG. 4 , in a third embodiment fire shield  90  includes an iris-like enclosure (shown only partially closed in  FIG. 4 ) which may be closed over oil cooler  26  in the event of a compartment fire to shield the cooler from the flames. 
   Referring to  FIG. 5 , in a fourth embodiment fire shield  90  includes an inflatable bladder  98  preferably comprised of a suitable fire resistant material such as Nomex™ (a trademark of E. I. du Pont de Nemours and Company) cloth or other suitable material. Actuator  100  may include a pyrotechnic type device roughly similar to that employed in automobile airbag restraint systems. 
   One skilled in the art will recognize that the teachings of the present invention may be incorporated into numerous other structural configurations, as well, such as shutters, scoop or deflector, butterfly valve(s) or other valve arrangements, and many other moveable and non-moveable shielding arrangements. Accordingly, the above embodiments are intended to be illustrative only. 
   The present invention is presented as beneficial to passive cooling systems of the type shown generally in  FIG. 1 . It will be appreciated, however, that air may be provided in any number of ways to the compartment. For example, scoop  60  and outlet  50  may be absent, and instead a separate conduit (not shown) provided which independently supplies air to compartment  12  (as shown, for example, U.S. Pat. No. 6,092,360, the contents of which incorporated by reference into this disclosure), or alternately, a louver (not shown) may be provided in exterior surface  16  of the aircraft (as shown, for example, U.S. Pat. No. 5,265,408, the contents of which also incorporated by reference into this disclosure). The means by which air is supplied to compartment  12  is not important to the present invention. Furthermore, the present invention may also be beneficially applied in other types of auxiliary power unit cooling systems. The scope of the appended claims is not intended to be limited, therefore, only to the specific embodiments described herein.