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An auxiliary power unit (APU) with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine intake air duct secured to an enclosure, the enclosure having a bleed air port extending from the combust

An auxiliary power unit (APU) with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine intake air duct secured to an enclosure, the enclosure having a bleed air port extending from the combustor to outside of the enclosure, with an APU secured therein. The APU can be retrofitted to existing aircraft, or installed in newly-built aircraft.

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We claim: 1. An auxiliary power unit and integral firebox, comprising: a turbomachine; a fireproof air intake duct at least partially surrounding the turbomachine, a turbomachine air intake duct having an aft end; a fireproof enclosure having an intake portion and surrounding the turbomachine; a fi

We claim: 1. An auxiliary power unit and integral firebox, comprising: a turbomachine; a fireproof air intake duct at least partially surrounding the turbomachine, a turbomachine air intake duct having an aft end; a fireproof enclosure having an intake portion and surrounding the turbomachine; a fireproof mounting portion adapted to coupling the aft end of the turbomachine air intake duct to the intake portion of the fireproof enclosure, the coupling comprising a fireproof sealant disposed between the fireproof mounting portion and the air intake duct, the fireproof mounting portion further adapted to couple the air intake duct and the fireproof enclosure to the turbomachine, wherein the coupling between the air intake duct and the fireproof enclosure comprises a plurality of fireproof joint; and a bleed port having an inlet end connected to a turbomachine bleed air supply, said bleed port extending from said inlet end through said fireproof enclosure to an outlet, wherein said bleed port further comprises a stub duct extending radially from a turbomachine bleed air takeoff duct to penetrate a bleed port aperture of said fireproof enclosure, said bleed port having a fireproof compressible seal disposed to said stub duct inboard of said fireproof enclosure. 2. The auxiliary power unit and integral firebox of claim 1, further comprising a mounting system to mount the auxiliary power unit and integral firebox to an aircraft. 3. The auxiliary power unit and integral firebox of claim 2, further comprising a fireproof sealant disposed between said mounting system and said turbomachine air intake duct. 4. The auxiliary power unit and integral firebox of claim 1 wherein said turbomachine air intake duct is formed into a single fiber reinforced plastic composite. 5. The auxiliary power unit and integral firebox of claim 1 wherein said fireproof compressible seal may be constructed of a glass fiber fabric woven about polycrystalline fibers. 6. The auxiliary power unit and integral firebox of claim 1 further comprising at least two cover plates to mate with one another and form a cylinder and interface with an outer surface of said enclosure and said fireproof compressible seal. 7. The auxiliary power unit and integral firebox of claim 1 wherein said fireproof enclosure has an inner surface to provide a structural backing capable of securing a thermal barrier. 8. The auxiliary power unit and integral firebox of claim 7 wherein said thermal baffler is constructed of a powder-filament mixture of amorphous silica, metal oxides, and glass filaments. 9. An auxiliary power unit, comprising: a turbomachine; a fireproof turbomachine air intake duct having an aft end, the fireproof turbomachine air intake duct surrounding the turbomachine; a firebox secured to the fireproof turbomachine air intake duct, the firebox comprising: a fireproof enclosure surrounding the turbomachine and coupled to the aft end of said fireproof turbomachine air intake duct via a fireproof mounting portion, said fireproof mounting portion additionally coupling to the turbomachine, wherein the coupling between the fireproof mounting portion and the fireproof turbomachine air intake duct comprises a plurality of fireproof ioints and a fireproof sealant is disposed therebetween; and a bleed port having an inlet end connected to a turbomachine bleed air supply, said bleed port extending from said inlet end through said fireproof enclosure to an outlet, wherein said bleed port further comprises a stub duct extending radially from a turbomachine bleed air takeoff duct to penetrate a bleed port aperture of said fireproof enclosure, said bleed port having a fireproof compressible seal disposed to said stub duct inboard of said fireproof enclosure. 10. The auxiliary power unit of claim 9, further comprising a mounting system configured for mounting the auxiliary power unit and firebox to an aircraft. 11. The auxiliary power unit of claim 9, further comprising an air intake duct flexible boot that is secured to an intake end. 12. The auxiliary power unit of claim 9 further comprising: an air intake flame arrestor secured within said fireproof turbomachine air intake duct and disposed between a staffer-generator unit and an intake end. 13. The auxiliary power unit of claim 9 further comprising: a cooling air intake duct extending forwardly from said fireproof enclosure.