Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
298 words
A gas turbine engine comprising: a housing having an air inlet and an exhaust outlet; fluid passage means formed through said housing between said inlet and said outlet; a low pressure spool assembly comprising a first shaft rotatably mounted in the housing, at least one low pressure compressor stage disposed in said fluid passage means and secured adjacent one end of said first shaft, and at least one low pressure turbine stage disposed in said fluid passage means and secured adjacent the other end of the shaft; an intermediate pressure spool assembly comprising a second shaft rotatably mounted in said housing, at least one intermediate pressure compressor stage disposed in said fluid passage means immediately downstream from said low pressure compressor stage and secured adjacent one end of said second shaft, at least one intermediate pressure turbine stage disposed in said fluid passageway upstream from said low pressure turbine stage and secured to said second shaft adjacent its other end; a high pressure spool assembly comprising a third shaft rotatably mounted in said housing, at least one high pressure compressor stage disposed in said fluid passage means downstream from said intermediate pressure compressor stage and secured adjacent one end of said third shaft, at least one high pressure turbine stage disposed in said fluid passage means upstream from said intermediate pressure turbine stage and secured to said third shaft adjacent its other end; combustor means for burning a fuel between said high pressure compressor and turbine stages; wherein said first and second shafts are coaxial with each other; and wherein the axis of said third shaft is substantially perpendicular and radially offset with respect to the axis of said first or second shaft so that said high pressure spool assembly straddles the low and intermediate pressure spool assemblies.
Claim 2
Dependent Claim
298 words
A gas turbine engine comprising: a housing having an air inlet and an exhaust outlet; fluid passage means formed through said housing between said inlet and said outlet; a low pressure spool assembly comprising a first shaft rotatably mounted in the housing, at least one low pressure compressor stage disposed in said fluid passage means and secured adjacent one end of said first shaft, and at least one low pressure turbine stage disposed in said fluid passage means and secured adjacent the other end of the shaft; an intermediate pressure spool assembly comprising a second shaft rotatably mounted in said housing, at least one intermediate pressure compressor stage disposed in said fluid passage means immediately downstream from said low pressure compressor stage and secured adjacent one end of said second shaft, at least one intermediate pressure turbine stage disposed in said fluid passageway upstream from said low pressure turbine stage and secured to said second shaft adjacent its other end; a high pressure spool assembly comprising a third shaft rotatably mounted in said housing, at least one high pressure compressor stage disposed in said fluid passage means downstream from said intermediate pressure compressor stage and secured adjacent one end of said third shaft, at least one high pressure turbine stage disposed in said fluid passage means upstream from said intermediate pressure turbine stage and secured to said third shaft adjacent its other end; combustor means for burning a fuel between said high pressure compressor and turbine stages; wherein said first and second shafts are coaxial with each other; and wherein the axis of said third shaft is substantially perpendicular and radially offset with respect to the axis of said first or second shaft so that said high pressure spool assembly straddles the low and intermediate pressure spool assemblies.
Claim 3
Dependent Claim
114 words
The invention as defined in claim 1 wherein said fluid passage means further comprises an inner flow channel and an outer flow channel, said intermediate pressure and high pressure spool assemblies being operatively disposed in said inner flow channel and said outer flow channel extending directly from said low pressure compressor and to said outlet and further comprising a housing part in which said high pressure spool assembly is contained, said housing part being positioned at least in part in said outer flow channel so that at least a portion of any heat loss from said housing part enters the air flow through the outer flow channel and augments the thrust from the outlet.
Claim 4
Dependent Claim
25 words
The invention as defined in claim 1 wherein said second shaft is tubular and wherein said first shaft extends coaxially entirely through said second shaft.
Claim 5
Dependent Claim
41 words
The invention as defined in claim 1 wherein said third shaft being wholly contained within said housing part, said housing part being completely closed at each axial end of the third shaft thereby eliminating any leakage axially from the housing part.
Claim 6
Dependent Claim
25 words
The invention as defined in claim 4 wherein an arcuate scroll tube fluidly connects said intermediate pressure compressor stage with said high pressure compressor stage.
Claim 7
Dependent Claim
25 words
The invention as defined in claim 5 wherein a second arcuate scroll tube fluidly connects said high pressure turbine stage with said intermediate turbine stage.
Claim 8
Dependent Claim
17 words
The invention as defined in claim 5 wherein said scroll tube is substantially circular in cross-sectional shape.
Claim 9
Dependent Claim
29 words
The invention as defined in claim 7 wherein the cross-sectional area of the scroll tube gradually varies from said intermediate pressure compressor stage to said high pressure compressor stage.
Claim 10
Dependent Claim
58 words
The invention as defined in claim 1 and further comprising a first arcuate scroll tube fluidly connecting said intermediate pressure compressor stage with said high pressure compressor stage and a second arcuate scroll tube fluidly connecting said high pressure turbine stage with said intermediate turbine stage and wherein said scroll tubes are substantially the same in lineal length.