REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM

Abstract

The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50) from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

Claims

1. A reverse-flow core gas turbine engine having an air inlet and an engine exhaust aft of the air inlet, the engine comprising: a. a low spool disposed aft of the air inlet including a rearward-flow low pressure compressor, and a forward-flow low pressure turbine disposed aft of the rearward-flow low pressure compressor; b. a high spool disposed aft of the low spool, the high spool including a forward-flow high pressure turbine disposed aft of the forward-flow low pressure turbine, a combustor disposed aft of the forward-flow high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor; c. an intake reverse-duct disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor so that the output reverses from rearward-flow to forward-flow to pass through the high spool; d. a discharge reverse-manifold disposed forward of the high spool and radially outward of the intake reverse-duct for receiving an exhaust gas stream from the forward-flow low pressure turbine and for directing the exhaust gas stream from forward-flow to rearward-flow toward the engine exhaust; e. a pulse detonation system including at least one pulse detonation firing tube secured in fluid communication with the reverse discharge-duct, the at least one pulse detonation firing tube positioned to be radially outward of and to overlie the high spool so that a portion of the pulse detonation firing tube intersects an axis that is perpendicular to an engine center line and which axis passes through the high spool; and, f. the at least one pulse detonation firing tube being configured to mix the exhaust gas stream with fuel so that the mixed fuel and exhaust gas stream pulse detonates as the mixed fuel and exhaust gas stream pass through the firing tube toward the engine exhaust.

2. The reverse-flow core gas turbine engine of claim 1, further comprising a plurality of pulse detonation firing tubes, wherein each of the plurality of firing tubes is positioned about an equal distance from adjacent firing tubes, and wherein the plurality of firing tubes are positioned to surround the high spool of the engine.

3. The reverse-flow core gas turbine engine of claim 2 wherein the plurality of pulse detonation firing tubes includes between about eleven and about twenty-two firing tubes.

4. The reverse-flow core gas turbine engine of claim 1, wherein the engine further comprises an annular bypass duct surrounding and extending radially outward of the low spool and the high spool that directs bypass air from the air inlet to the exhaust of the engine, and wherein the one or more pulse detonation firing tubes are positioned within the annular bypass duct and exposed to cooling air passing through the bypass duct.

5. The reverse-flow core gas turbine engine of claim 1, further comprising a plurality of pulse detonation firing tubes and wherein the plurality of firing tubes comprise constant volume combustor tubes.

6. The reverse-flow core gas turbine engine of claim 1, further comprising a plurality of groups of adjacent pulse detonation firing tubes, each of the plurality of groups of adjacent firing tubes being positioned so that each group is about an equal distance from a closest group of firing tubes, and the groups of adjacent pulse detonation firing tubes being positioned to surround the high spool of the engine.

7. A reverse-flow core gas turbine engine having an air inlet and an engine exhaust aft of the air inlet, the engine comprising: a. a low spool disposed aft of the air inlet including a rearward-flow low pressure compressor, a forward-flow low pressure turbine disposed aft of the rearward-flow low pressure compressor and a low pressure shaft secured between the low pressure turbine and the low pressure compressor; b. a high spool disposed aft of the low spool, the high spool including a forward-flow high pressure turbine disposed aft of the forward-flow low pressure turbine, a combustor disposed aft of the forward-flow high pressure turbine, a forward-flow high pressure compressor disposed aft of the combustor, and a high pressure shaft secured between the high pressure turbine and the high pressure compressor; c. an intake reverse-duct disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor so that the output reverses from rearward-flow to forward-flow to pass through the high spool; d. a discharge reverse-manifold disposed forward of the high spool and radially outward of the intake reverse-duct for receiving an exhaust gas stream from the forward-flow low pressure turbine and for directing the exhaust gas stream from forward-flow to rearward-flow toward the engine exhaust; e. a pulse detonation system including at least one pulse detonation firing tube secured in fluid communication with the reverse discharge-duct, the at least one pulse detonation firing tube positioned to be radially outward of and to overlie the high spool so that a portion of the pulse detonation firing tube intersects an axis that is perpendicular to an engine center line and which axis passes through the high spool; f. the at least one pulse detonation firing tube being configured to mix the exhaust gas stream with fuel so that the mixed fuel and exhaust gas stream pulse detonates as the mixed fuel and exhaust gas stream pass through the firing tube toward the engine exhaust; and, g. wherein flow through the engine extends sequentially through the rearward-flow low pressure compressor in a downstream direction, through the intake reverse-duct to the forward-flow high pressure compressor, the combustor, the forward-flow high pressure turbine and the forward-flow low pressure turbine in a forward direction, and through the discharge reverse-manifold to a rearward direction through the at least one pulse detonation firing tube.

8. The reverse-flow core gas turbine engine of claim 7, further comprising a plurality of pulse detonation firing tubes, wherein each of the plurality of firing tubes is positioned about an equal distance from adjacent firing tubes, and wherein the plurality of firing tubes are positioned to surround the high spool of the engine.

9. The reverse-flow core gas turbine engine of claim 8, wherein the engine further comprises an annular bypass duct surrounding and extending radially outward of the low spool and the high spool that directs bypass air from the air inlet to the exhaust of the engine, and wherein the one or more pulse detonation firing tubes are positioned within the annular bypass duct and exposed to cooling air passing through the bypass duct.

10. The reverse-flow core gas turbine engine of claim 7, wherein the one or more pulse detonation firing tubes comprise pulse detonation shock tubes.

11. A method of operating a reverse-flow gas turbine engine, the method comprising: a. directing flow of inlet air through an air inlet of the engine; b. then, compressing the air in a downstream direction through a rearward-flow low pressure compressor of a low spool of the engine; c. then, directing flow of the compressed air through an intake reverse-duct, and then into a forward-flow high pressure compressor, then combusting the compressed air by directing the compressed air with fuel through a combustor, then directing a combusted gas stream from the combustor and through a forward-flow high pressure turbine of a high spool, and then through a forward-flow low pressure turbine in a forward direction; c. then, directing the exhaust gas stream from the forward-flow low pressure turbine through a discharge reverse-manifold and then in a rearward direction through at least one pulse detonation firing tube overlying the high spool; and, d. mixing the exhaust gas stream with fuel within the at least one pulse detonation firing tube and pulse detonating the mixed fuel and exhaust gas stream within the at least one pulse detonation firing tube.

12. A method of operating the reverse-flow gas turbine engine of claim 11, further comprising directing a flow of bypass air through a bypass duct and positioning the at least one pulse detonation firing tube within the bypass duct.

13. A method of operating the reverse-flow gas turbine engine of claim 11, further comprising directing the exhaust gas stream from the forward-flow low pressure turbine through a plurality of pulse detonation firing tubes positioned about an equal distance from adjacent firing tubes and positioned to surround the high spool of the engine.

14. A method of operating the reverse-flow gas turbine engine of claim 11, further comprising directing the exhaust gas stream from the forward-flow low pressure turbine through a plurality of groups of adjacent pulse detonation firing tubes positioned so that each group is about an equal distance from a closest group of firing tubes, and positioned to surround the high spool of the engine.

15. A method of operating the reverse-flow gas turbine engine of claim 11, wherein the step of directing the exhaust gas stream through at least one pulse detonation firing tube overlying the high spool further comprises generating shock waves within the at least one pulse detonation firing tube.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0020] FIG. 1 is a simplified, schematic drawing of a reverse-flow core gas turbine engine with a pulse detonation system constructed in accordance with the present disclosure.

[0021] FIG. 2 is a simplified, schematic, cross-sectional view of a reverse-flow core gas turbine engine with a pulse detonation system, showing twelve pulse detonation firing tubes surrounding a core of the engine.

[0022] FIG. 3 is a simplified, schematic, cross-sectional view of a reverse-flow core gas turbine engine with a pulse detonation system, showing twelve groups of adjacent pulse detonation firing tubes surrounding a core of the engine.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0023] Referring to the drawings in detail, FIG. 1 shows a simplified, schematic representation of a reverse-flow core gas turbine engine with a pulse detonation system, and is generally designated by reference numeral 10. The engine 10 includes an air inlet 12 and an engine exhaust 14 aft of the air inlet 12. The engine 10 also includes a low spool 16 disposed aft of the air inlet 12. (For purposes herein, the word aft, such as used in the previous sentence, is to mean that the low spool 16 is disposed within the engine 10 at a position relative to the air inlet 12 that is closer to the engine exhaust 14 than is the air inlet 12.)

[0024] The low spool 16 has a rearward-flow low pressure compressor 18. (For purposes herein the phrase rearward-flow, as used in the previous sentence, is to mean that flow of air through the low pressure compressor flows in a direction toward the engine exhaust 14.) The low spool 16 also includes a forward-flow low pressure turbine 20 disposed aft of the rearward-flow low pressure compressor 18. (For purposes herein, the phrase forward-flow, as used in the previous sentence, is to mean that flow through the low pressure turbine 20 is in a direction toward the air inlet 12 of the engine 10.) The low spool 16 also has a low pressure shaft 22 that is secured between the low pressure turbine 20 and the low pressure compressor 18. The engine 10 may also include a gear shaft 24 secured between the low pressure compressor 18 and a fan gear box 26 for controlling a fan shaft 23 to rotate a fan 30 within the air inlet 12. The engine 10 may also include fan guide vanes 32A, 32B secured within the air inlet 12 adjacent opposed sides of the fan 30, if the engine 10 is a turbo fan form of a gas turbine engine.

[0025] The engine also includes a high spool 34 disposed aft of the low spool 16. The high spool 34 has a forward-flow high pressure turbine 36 disposed aft of the forward-flow low pressure turbine 20. A combustor 38 is disposed aft of the forward-flow high pressure turbine 36, and a forward-flow high pressure compressor 40 is disposed aft of the combustor 38. The high spool 34 also has a high pressure shaft 42 secured between the high pressure turbine 36 and the high pressure compressor 40. (It is noted that FIG. 1 is a schematic, simplified representation of the present disclosure. Components, such as the low pressure shaft 22 and high pressure shaft 42 are shown schematically only, and their representation in FIG. 1 is only to show relative interconnections, and is not to be interpreted as representing an actual shape or form of the shafts 22, 42 or of any other components.) The exemplary reverse-flow core gas turbine engine 10 generally includes the low speed spool 16 and the high spool 34 mounted for rotation about an engine central longitudinal axis 52 relative to an engine static structure 100 or housing via a plurality of bearing systems, such as a first bearing system 102, a second bearing system 104 (including a, a third bearing system 106, a fourth bearing system 108 and a fifth bearing system 110. It is to be understood that various bearing systems at various engine 10 locations may alternatively or additionally be provided.

[0026] An intake reverse-duct 44 is disposed radially outward of the high spool 34 and is configured for directing output of the rearward-flow low pressure compressor 18 to flow into the forward-flow high pressure compressor 40. In other words, the output of the low pressure compressor 13 reverses flow within the intake reverse-duct 44 to pass through the high spool 34 in a forward direction. FIG. 1 includes direction of flow arrows 46 for working air passing through the engine 10 and the arrows 46 show the change of direction of the working air passing through the intake reverse-duct 44.

[0027] A discharge reverse-manifold 48 is disposed forward of the high spool 34 and extends radially outward of the intake reverse-duct 44 for receiving an exhaust gas stream 50 from the forward-flow low pressure turbine 20 and for directing the exhaust gas stream 50 toward the engine exhaust 14. (For purposes herein, the phrase radially outward, as used in the previous sentence, is to mean that the identified component, namely the extension of the discharge reverse-manifold 48, is further from the engine 10 longitudinal axis or center line 52 than is the intake reverse-duct 44.)

[0028] At least one pulse detonation firing tube 54 is secured in fluid communication with the reverse discharge-duct 48. The at least one pulse detonation firing tube 54 is positioned to overlie the high spool 34. (For purpose herein, the word overlie as used in the previous sentence, is to mean that at least a portion 56 of the pulse detonation firing tube 54 intersects an axis 58 that is perpendicular to the center line 52 and that passes through the high spool 34.) The firing tube 54 is also configured to mix the exhaust gas stream 50 with fuel, received through a fuel inlet 60 in the tube 54, so that the mixed fuel and exhaust gas stream 50 pulse detonates as the mixed fuel and exhaust gas stream 50 are directed by control valves 51 through the firing tube 54 and out of the firing tube 54 through an outlet end 62 of the tube 54. The detonated exhaust gas stream 50 passes through the tube 54 in a direction toward the engine exhaust 14. Pulsed detonation of the exhaust gas stream 50 produces a pressure increase in the exhaust stream within the tube 54 that results in enhanced thrust for the engine 10 as the detonated exhaust stream passes out of the outlet end 62 of the firing tube 54.

[0029] As described above, flow of the working gas, such as the atmosphere, through the engine 10, as shown by the flow direction arrows 46, extends sequentially first through the rearward-flow low pressure compressor 18 in a downstream direction toward the engine exhaust 12. Then, the flow moves through the intake reverse-duct 44 to the forward-flow high pressure compressor 40, then the combustor 38, the forward-flow high pressure turbine 36 and then the forward-flow low pressure turbine 20 in a forward direction, or toward the air inlet 12. After combustion in the combustor 38, the working gas is referred to as the exhaust gas stream 50 and flows through the discharge reverse-manifold 48 to flow in a rearward direction through the at least one pulse detonation firing tube 54.

[0030] FIG. 2 shows a cross-sectional view of an alternative, multi-tube embodiment 64 of a reverse-flow core gas turbine engine with a pulse detonation system 64. In the multi-tube embodiment 64, the engine 64 may include a plurality of pulse detonation firing tubes 66 surrounding a high spool 68 of the multi-tube engine 64 and positioned between the high spool 68 and an outer casing 69 within a bypass air cooling passage 71. As shown in FIG. 2, each of the plurality of firing tubes 66 is positioned about an equal distance from adjacent firing tubes 66. An exemplary number of firing tubes 66 is between about 11 and about 22.

[0031] FIG. 3 shows a second alternative multi-tube embodiment 164 of a reverse-flow core gas turbine engine with a pulse detonation system 164. In the FIG. 3 embodiment of the engine 164, a plurality of groups 166 of adjacent pulse detonation firing tubes 167, such as a group 166 including a pair of adjacent tubes 167, or a group including three tubes 67 (not shown), etc. Each of the plurality of groups 166 of adjacent firing tubes 167 is positioned so that each group 166 is about an equal distance from a closest group 166 of firing tubes 167, and wherein the plurality of groups 166 of firing tubes are positioned to surround the high spool 163 of the second multi-tube embodiment 164. An exemplary number of groups 166 of adjacent firing tubes 167 is between about 11 and about 22. As with the FIG. 2 embodiment, the FIG. 3 embodiment also includes an outer casing 169 that defines a cooling passage 171 between the casing 169 and the high spool 168.

[0032] As shown in FIG. 1, the at least one pulse detonation tube 54, as well as the plurality of tubes 66 in FIG. 2, may be a shock tube 54 utilizing shock-tube components 70 to generate shock waves for detonating the exhaust gas stream 50 and fuel added through the fuel inlet 60 to the tube 54. As is known to those skilled in the art, the shock tube 54 may accomplish pulse detonation of the gas and fuel in various types of detonation chambers (not shown). Such chambers include detonation tubes 54, 66, 167 resonating detonation cavities, annular detonation chambers, etc. The shock tube 54 may have a circular cross-sectional profile. The pulse detonation firing tube 54 or shock tube 54 may also be constant volume combustor tubes, using the same components for each firing tube 54, but with different timing of the control valve 51.

[0033] FIG. 1 also shows that the engine 10 may include an annular bypass duct 72 surrounding and extending radially outward of the low spool 16 and the high spool 34. The bypass duct 72 directs bypass air from the air inlet 12 to the exhaust 14 of the engine 10. FIG. 1 also includes direction of flow arrows 74 for by-pass air passing through the engine 10 from the air inlet 12 to the engine exhaust 14. FIG. 1 shows that the one or more pulse detonation firing tubes 54 are positioned within the annular bypass duct 72 and are exposed to cooling air passing through the bypass duct 72. FIG. 1 also shows a nozzle 90 including an outline of an exhaust nozzle 92 which receives flow from the engine exhaust 14 and the mixed flow of the by-pass air and the exhaust gas stream 50. It is to be understood that various fixed, variable, convergent/divergent, two-dimensional and three-dimensional exhaust nozzles may be utilized herewith.

[0034] As described above, there is no need to admit oxygen or atmospheric air in to the firing tubes because the flow exiting the forward-flow low pressure turbine 20 is substantially below the stoichiometric fuel to air ratio (e.g., 0.067) necessary for detonation of the exhaust gas stream 50. The pulse detonation firing tube 54, or groups 166 of adjacent firing tubes 167, fuel inlet 60 on the tube 54, pre-detonation section 76 of the tube 54, Shockwave components 70 and outlet end 62 of the tube 54 form a pulse detonation system 80 of the reverse-flow core gas turbine engine 10.

[0035] The present disclosure also provides for a method of operating the gas turbine engine 12 including a sequence of steps. The sequence includes, first, directing flow of the inlet air through the air inlet 12 of the engine 10 and then compressing the air through the rearward-flow low pressure compressor 18 in a downstream direction. Second, then directing flow of the compressed air through the intake reverse-duct 44, and then into the forward-flow high pressure compressor 40. The compressed, high pressure air is then directed into the combustor 38 and is combusted therein with fuel. The combusted exhaust gas stream 50 is then directed through the forward-flow high pressure turbine 36 and then through the forward-flow low pressure turbine 20 in a forward direction. The exhaust gas stream 50 is then directed forward of the low pressure turbine 20 and through the discharge reverse-manifold 48 and then in a rearward direction overlying the high spool 34 through the at least one pulse detonation firing tube 54 or groups 166 of adjacent firing tubes 167. Then the fuel and exhaust gas stream 50 mixtures is pulse detonated within the at least one pulse detonation tube 54 or groups 166 of adjacent tubes 167. The detonated exhaust gas stream 50 is directed out of the outlet end 62 of the firing tube 54 and out the engine 10 through the engine exhaust 14.

[0036] By having the pulse detonation firing tube 54 and/or the plurality of pulse detonation firing tubes 66 positioned to overlie the high spool 34, 68, the present disclosure provides for a substantially reduced overall axial length of the engine 10 between the air inlet 12 and the engine exhaust 14, while increasing the thrust of the engine 10 through use of the pulse detonation firing system 80. Additionally, by having the pulse detonation system 80 positioned within the bypass air duct 72, the present disclosure provides for extraordinarily efficient cooling of the pulse detonation firing tubes 54 within the compact profile of the present reverse-flow core gas turbine engine 10.

[0037] While the above disclosure has been presented with respect to the described and illustrated embodiments of a reverse-flow core gas turbine engine 10 with a pulse detonation system 80, it is to be understood that the disclosure is not to be limited to those alternatives and described embodiments. For example, while the engine 10 includes a fan 30 and fan gear box 26 to drive the fan from the low pressure compressor 18, it is to be understood that the present disclosure applies to all forms of reverse flow core gas turbine engines, including turbo fans, etc. Accordingly, reference should be made primarily to the following claims rather than the foregoing description to determine the scope of the disclosure.