Gas turbine engine configurations
First Claim
1. A gas turbine engine, comprising:
- at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine;
at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools;
a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and
a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;
a first inlet gas to a first compressor in the first turbo-compressor spool enters the first compressor along a first axis;
a first compressed gas from the first compressor exits the first compressor along a second axis;
the first compressed gas to a second compressor in the second turbo-compressor spool enters the second compressor along a third axis;
a second compressed gas from the second compressor exits the second compressor along a fourth axis; and
wherein the second axis is rotatable about the first axis and fourth axis is rotatable about the third axis.
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Accused Products
Abstract
A system of dense packaging of turbomachinery in a gas turbine engine by means of close-coupling of components and by the ability to rotate various engine components with respect to other engine components is disclosed. In addition, spool shaft rotational direction may be reversed to suit the application. In multiple engine configurations, the same ability to close-couple and rotate components and to reverse shaft rotational direction in order to rearrange the engine geometry package is used for packaging two or more gas turbine engines to achieve high power density. Dense-packing is possible because of a number of features of the basic engine. These features include: the use of compact centrifugal compressors and radial turbine assemblies; the close coupling of turbomachinery for a dense packaging; the ability to rotate certain key components so as to facilitate ducting and preferred placement of other components; the ability to control spool shaft rotational direction; and operation at high overall pressure ratios.
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Citations
34 Claims
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1. A gas turbine engine, comprising:
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at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;a first inlet gas to a first compressor in the first turbo-compressor spool enters the first compressor along a first axis; a first compressed gas from the first compressor exits the first compressor along a second axis; the first compressed gas to a second compressor in the second turbo-compressor spool enters the second compressor along a third axis; a second compressed gas from the second compressor exits the second compressor along a fourth axis; and wherein the second axis is rotatable about the first axis and fourth axis is rotatable about the third axis. - View Dependent Claims (2, 3, 4)
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5. A gas turbine engine, comprising:
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at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; a first expanded gas from the first turbine exits the first turbine along a sixth axis; the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; a second expanded gas from the second turbine exits the second turbine along an eighth axis; and wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis. - View Dependent Claims (6, 7, 8)
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9. A power unit comprising:
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(a) a first gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and ix wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (b) a second gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; wherein the first gas turbine engine and the second gas turbine engine are positioned side-by-side; and wherein the recuperator of the first gas turbine engine and the recuperator of the second gas turbine engine are positioned side-by-side with adjacent sides of the recuperator of the first gas turbine engine and the recuperator of the second gas turbine engine being substantially parallel to one another. - View Dependent Claims (10, 11, 12)
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13. A power unit comprising:
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(a) a first gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (b) a second gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; wherein the first gas turbine engine and the second gas turbine engine are positioned side-by-side; and wherein the intercooler of first gas turbine engine and the intercooler of second gas turbine engine are positioned side-by-side with adjacent sides of the intercooler of first gas turbine engine and the intercooler of second gas turbine engine being substantially parallel to one another. - View Dependent Claims (14, 15, 16)
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17. A power unit comprising:
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(a) a first gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (x) a free power spool associated with the radial turbine comprising a radial turbine, a variable area nozzle and a mechanical power output shaft; (xi) an inlet gas to the radial turbine enters the radial turbine along a ninth axis; (xii) an expanded gas exits the radial turbine along a tenth axis; and (xiii) wherein the ninth axis is rotatable about the tenth axis and the rotational direction of the mechanical power output shaft about the tenth axis can be reversed; (b) a second gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (x) a free power spool associated with the radial turbine comprising a radial turbine, a variable area nozzle and a mechanical power output shaft; (xi) an inlet gas to the radial turbine enters the radial turbine along a ninth axis; (xii) an expanded gas exits the radial turbine along a tenth axis; and (xiii) wherein the ninth axis is rotatable about the tenth axis and the rotational direction of the mechanical power output shaft about the tenth axis can be reversed; wherein the first gas turbine engine and the second gas turbine engine are positioned side-by-side; and wherein the mechanical power output shaft of the free power spool of the first gas turbine engine and the mechanical power output shaft of the free power spool of the second gas turbine engine are substantially parallel to their respective exhaust pipes and substantially perpendicular to an inlet of at least one of the centrifugal compressors of the first gas turbine engine and the second gas turbine engine. - View Dependent Claims (18, 19, 20)
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21. A power unit comprising:
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(a) a first gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (x) a free power spool associated with the radial turbine comprising a radial turbine, a variable area nozzle and a mechanical power output shaft; (xi) an inlet gas to the radial turbine enters the radial turbine along a ninth axis; (xii) an expanded gas exits the radial turbine along a tenth axis; and (xiii) wherein the ninth axis is rotatable about the tenth axis and the rotational direction of the mechanical power output shaft about the tenth axis can be reversed; (b) a second gas turbine engine comprising; (i) at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine; (ii) at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools; (iii) a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and (iv) a combustor operable to combust a fuel in the presence of the further heated gas;
wherein;(v) a first inlet gas to a first turbine in the first turbo-compressor spool enters the first turbine along a fifth axis; (vi) a first expanded gas from the first turbine exits the first turbine along a sixth axis; (vii) the first expanded gas to a second turbine in the second turbo-compressor spool enters the second turbine along a seventh axis; and (viii) a second expanded gas from the second turbine exits the second turbine along an eighth axis; and (ix) wherein the fifth axis is rotatable about the sixth axis and seventh axis is rotatable about the eighth axis; (x) a free power spool associated with the radial turbine comprising a radial turbine, a variable area nozzle and a mechanical power output shaft; (xi) an inlet gas to the radial turbine enters the radial turbine along a ninth axis; (xii) an expanded gas exits the radial turbine along a tenth axis; and (xiii) wherein the ninth axis is rotatable about the tenth axis and the rotational direction of the mechanical power output shaft about the tenth axis can be reversed; wherein the first gas turbine engine and the second gas turbine engine are positioned side-by-side; and wherein the mechanical power output shaft of the free power spool of the first gas turbine engine and the mechanical power output shaft of the free power spool of the second gas turbine engine are substantially perpendicular to their respective exhaust pipes and substantially perpendicular to an inlet of at least one of the centrifugal compressors of the first gas turbine engine and the second gas turbine engine. - View Dependent Claims (22, 23, 24)
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25. A method, comprising:
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providing a first gas turbine engine in a first gas turbine engine configuration, the gas turbine engine having; a first turbo-compressor spool with a first centrifugal compressor in mechanical communication with a first radial turbine, a second turbo-compressor spool with a second centrifugal compressor in mechanical communication with a second radial turbine, at least one intercooler positioned in a fluid path between the first and second turbo-compressor spools, a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by at least one of the first and second turbo-compressor spools and thereby form a further heated gas, and a combustor operable to combust a fuel in the presence of the further heated gas, transferring a first inlet gas to the first compressor along a first axis thereof; transferring a first compressed gas from an exit of the first compressor along a second axis thereof; transferring the first compressed gas to the second compressor along a third axis thereof, wherein the second axis has a first orientation relative to the first axis; transferring a second compressed gas from an exit of the second compressor along a fourth axis thereof, wherein the third axis has a first orientation relative to the fourth axis; and rotating at least one of (a) the second axis about the first axis to provide a second gas turbine engine configuration in which the second axis has a second orientation relative to the first axis, and (b) the third axis about the fourth axis to provide a third gas turbine engine configuration in which the third axis has a second orientation relative to the fourth axis. - View Dependent Claims (26, 27, 28, 29)
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30. A method, comprising:
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providing a first gas turbine engine in a first gas turbine engine configuration, the gas turbine engine having; a first turbo-compressor spool with a first centrifugal compressor in mechanical communication with a first radial turbine, a second turbo-compressor spool with a second centrifugal compressor in mechanical communication with a second radial turbine, at least one intercooler positioned in a fluid path between the first and second turbo-compressor spools, a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by at least one of the first and second turbo-compressor spools and thereby form a further heated gas, and a combustor operable to combust a fuel in the presence of the further heated gas, transferring a first inlet gas to the first radial turbine along a fifth axis thereof; transferring a first compressed gas from an exit of the first radial turbine along a sixth axis thereof, wherein the fifth axis has a first orientation relative to the sixth axis; transferring the first compressed gas to the second radial turbine along a seventh axis thereof; transferring a second compressed gas from an exit of the second radial turbine along an eighth axis thereof, wherein the seventh axis has a first orientation relative to the eighth axis; and rotating at least one of (a) the fifth axis about the sixth axis to provide a second gas turbine engine configuration in which the fifth axis has a second orientation relative to the sixth axis, and (b) the seventh axis about the eighth axis to provide a third gas turbine engine configuration in which the seventh axis has a second orientation relative to the eighth axis. - View Dependent Claims (31, 32, 33, 34)
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Specification