Turbofan with gear-driven compressor and fan-driven core

• US 9,003,808 B2
• Filed: 11/02/2011
• Issued: 04/14/2015
• Est. Priority Date: 11/02/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kupratis, Daniel B.
• Primary Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US13/287,446
• Publication Number:
  US 20130104524A1
• Time in Patent Office: 1,259 Days
• Field of Search: 607/92, 60/391.63, 602/261, 60/394.3
• US Class Current: 60/792
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02K 3/077 the plant being of the multiple flow type, i.e. having three or more flows
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine comprises an outer engine case, a combustor, a high pressure spool and a low pressure spool. The combustor is disposed within the outer engine case. The high pressure spool is configured for rotation coaxially with the combustor. The low pressure spool is configured for rotation coaxially with the high pressure spool. The low pressure spool is configured to rotate at speeds faster than that of the high pressure spool during operation of the gas turbine engine. In one embodiment, the low pressure spool includes a gear system configured to rotate a low pressure compressor faster than a low pressure turbine. In another embodiment, the high pressure spool rotates outward of the combustor within the outer engine case. In another embodiment, the high pressure spool includes a drum having radially inward projecting blades and vanes and radially outward projecting fan blades.

Claims

1. A gas turbine engine comprising:

an outer engine case;

an inner engine case coupled to the outer case radially inward of the outer engine case;

a combustor disposed between the outer engine case and the inner engine case;

a high pressure spool having an annular drum configured for rotation within the outer engine case;

wherein the annular drum has an axially-extending portion configured for rotation outward of the combustor; and

a low pressure spool having a drive shaft configured for rotation inward of the inner engine case.

2. The gas turbine engine of claim 1 wherein the drive shaft rotates at speeds faster than that of the annular drum during operation of the gas turbine engine.

3. The gas turbine engine of claim 2 wherein the low pressure spool comprises:

a low pressure turbine blade array extending from the drive shaft;

a low pressure compressor blade array extending from a stub shaft; and

a gear system coupling the drive shaft to the stub shaft and configured so that the stub shaft rotates at speeds faster than that of the drive shaft during operation of the gas turbine engine.

4. The gas turbine engine of claim 1 wherein the high pressure spool further comprises:

a plurality of compressor blades extending radially inward from a rotor and disposed upstream of the combustor, wherein the rotor is disposed radially inward from the axially-extending portion of the annular drum; and

a plurality of turbine blades extending radially inward from the annular drum downstream of the combustor, wherein the annular drum extends axially between the outer engine case and the inner engine case.

5. The gas turbine engine of claim 4 wherein the high pressure spool further comprises:

a fan stage driven by the high pressure spool between the outer engine case and the inner engine case, the fan stage comprising a plurality of fan blades extending radially outwardly from the annular drum.

6. The gas turbine engine of claim 5 and further comprising:

a plurality of compressor vanes extending radially outward from the inner engine case to engage the plurality of compressor blades and form a high pressure compressor;

a plurality of turbine vanes extending radially outward from the inner engine case to engage the plurality of turbine blades and form a high pressure turbine; and

a plurality of fan vanes extending radially inward from the outer engine case to engage the plurality of fan blades.

7. The gas turbine engine of claim 4 wherein the inner engine case comprises:

a forward duct;

an aft duct;

a support strut connecting the forward duct to the aft duct so that the aft duct is radially inward of the forward duct;

a forward strut connecting the forward duct to the outer engine case;

an aft strut connecting the aft duct to the outer engine case;

a plurality of low pressure compressor vanes extending radially inward from the forward duct;

a plurality of high pressure compressor vanes extending radially outward from the aft duct;

a plurality of high pressure turbine vanes extending radially outward from the aft duct;

a first bearing coupled to the forward duct; and

a second bearing coupled to the aft duct;

wherein the high pressure spool is disposed axially between the forward strut and the aft strut on the first and second bearings.

8. The gas turbine engine of claim 7 wherein the inner engine case further comprises:

an elbow joining the forward duct to the first bearing and the forward strut;

an inlet guide vane extending radially inward from the forward duct; and

a nose extending from the inlet guide vane.

9. The gas turbine engine of claim 1 wherein the low pressure spool further comprises:

a gear system coupled to the drive shaft, wherein the drive shaft extends axially within the inner engine case;

a stub shaft coupled to the gear system;

a plurality of turbine blades extending radially outward from the drive shaft downstream of the combustor; and

a plurality of compressor blades extending radially outward from the stub shaft upstream of the combustor.

10. The gas turbine engine of claim 9 and further comprising:

a plurality of turbine vanes extending radially inward from the outer engine case to engage the plurality of turbine blades and form a low pressure turbine; and

a plurality of compressor vanes extending radially inward from the inner engine case to engage the plurality of compressor blades and to form a low pressure compressor.

11. The gas turbine engine of claim 9 wherein:

the gear system comprises a planetary gear system that increases a rotational speed of the plurality of compressor blades over a rotational speed of the plurality of turbine blades.

12. The gas turbine engine of claim 9 wherein the outer engine case comprises:

an annular outer duct extending from an upstream end to a downstream end;

a plurality of vanes extending radially inward from the annular outer duct;

first and second struts extending radially inward from the annular outer duct downstream of the plurality of vanes;

an annular inner duct coupled to the annular outer duct via the first and second struts to form a bypass duct;

a plurality of vanes extending radially inward from the annular inner duct;

an aft strut extending radially inward from the annular outer duct;

an aft bearing coupled to the aft strut;

a forward strut extending radially inward form the annular outer duct; and

a forward bearing coupled to the forward strut;

wherein the aft bearing and the forward bearing support the low pressure spool within the inner engine case.

13. The gas turbine engine of claim 1 and wherein the high pressure spool further comprises:

a high pressure turbine blade array;

a high pressure compressor blade array, wherein the annular drum connects the high pressure turbine blade array and the high pressure compressor blade array; and

a fan stage extending from the annular drum.

14. The gas turbine engine of claim 1 wherein the low pressure spool further comprises:

a low pressure turbine blade array;

a low pressure compressor blade array;

a stub shaft extending from the low pressure compressor blade array; and

a planetary gear system coupling the drive shaft to the stub shaft.

15. A turbofan engine comprising:

a combustor for producing gas;

a high pressure turbine configured to be rotationally driven by the gas;

a high pressure compressor;

a high spool shaft coupling the high pressure turbine to the high pressure compressor;

a low pressure turbine configured to be rotationally driven by the gas leaving the high pressure turbine;

a low spool shaft coupled to the low pressure turbine;

a low pressure compressor;

a gear system coupling the low pressure compressor to the low spool shaft; and

a fan stage driven by the high spool shaft.

16. The turbofan engine of claim 15 wherein the gear system comprises:

a ring gear anchored to a non-rotating component of the turbofan engine;

a gear carrier configured to be driven by the low pressure turbine;

a plurality of planet gears mounted to the gear carrier; and

a sun gear disposed within the plurality of planet gears so as to drive the low pressure compressor at a speed higher than that of the high pressure turbine.

17. The turbofan engine of claim 15 wherein the high spool shaft comprises:

an annular drum comprising a forward end and an aft end; and

a cone section extending from the forward end of the annular drum;

a plurality of fan blades extending radially outward from the cone section;

a compressor disk extending radially inward from the forward end of the annular drum;

an annular rotor connected to the compressor disk;

a plurality of compressor blades extending radially inward from the annular rotor;

a plurality of turbine blades extending radially inward from the aft end of the annular drum; and

a turbine disk extending radially inward from one of the plurality of turbine blades.

18. The turbofan engine of claim 17 wherein the high spool shaft is configured to rotate radially outward of the combustor.

19. The turbofan engine of claim 15 wherein the low pressure compressor comprises:

an annular shaft portion;

a first radial projection extending from a forward end of the annular shaft portion to join to the gear system;

a cone portion extending from an aft end of the annular shaft portion;

a plurality of compressor blades extending radially outward from the cone portion; and

a rotor disk extending radially inward from the cone portion to a bearing.

20. The turbofan engine of claim 15 and further comprising an outer engine case comprising:

an annular outer duct extending from an upstream end to a downstream end;

first and second struts extending radially inward from the annular outer duct downstream of the plurality of vanes;

an annular inner duct coupled to the annular outer duct via the first and second struts to form a bypass duct;

an aft strut extending radially inward from the annular outer duct;

an aft bearing coupled to the aft strut;

a forward strut extending radially inward form the annular outer duct; and

a forward bearing coupled to the forward strut;

wherein the aft bearing and the forward bearing support the low pressure turbine and the low pressure compressor.

21. The turbofan engine of claim 15 and further comprising an inner engine case comprising:

a forward duct;

an aft duct;

a support strut connecting the forward duct to the aft duct so that the aft duct is radially inward of the forward duct;

a forward strut extending radially outward from the forward duct forward of the fan stage;

an aft strut extending radially outward from the aft duct aft of the high pressure turbine;

a first bearing coupled to the forward duct; and

a second bearing coupled to the aft duct;

wherein the high pressure turbine and the high pressure compressor are disposed axially between the forward strut and the aft strut on the first and second bearings.

22. The turbofan engine of claim 15 wherein the low pressure compressor rotates at speeds faster than that of the low pressure turbine during operation of the gas turbine engine.

23. The turbofan engine of claim 15 wherein the high spool shaft rotates radially outward of the combustor and the low spool shaft rotates radially inward of the combustor.

24. A gas turbine engine comprising:

an outer engine case;

a combustor disposed within the outer engine case;

a low pressure spool configured for rotation coaxially with the combustor; and

a high pressure spool configured for rotation coaxially with the low pressure spool, the high pressure spool comprising;

an annular drum extending axially between a forward end and an aft end radially outward of the combustor;

a plurality of compressor blades extending radially inward from the drum upstream of the combustor;

a plurality of turbine blades extending radially inward from the drum downstream of the combustor; and

a plurality of fan blades extending radially outwardly from the annular drum.

25. The gas turbine engine of claim 24 wherein:

the low pressure spool comprises;

a low pressure turbine having a drive shaft;

a low pressure compressor having a stub shaft; and

a gear system coupling the drive shaft to the stub shaft and configured so that the stub shaft rotates at speeds faster than that of the drive shaft during operation of the gas turbine engine, wherein the stub shaft is configured to rotate at speeds faster than that of the high pressure spool during operation of the gas turbine engine.

26. A gas turbine engine comprising:

an outer engine case;

a combustor disposed within the outer engine case;

a high pressure spool configured for rotation coaxially with the combustor; and

a low pressure spool configured for rotation coaxially with the high pressure spool, the low pressure spool comprising;

a low pressure turbine having a drive shaft;

a low pressure compressor having a stub shaft; and

a gear system having a sun gear, a ring gear, a plurality of planet gears, and a gear carrier, wherein the gear system couples the drive shaft to the stub shaft and is configured so that the stub shaft rotates at speeds faster than that of the drive shaft during operation of the gas turbine engine, and wherein the sun gear connects to the stub shaft and the gear carrier connects to the drive shaft.

27. A gas turbine engine comprising:

an outer engine case;

a combustor disposed within the outer engine case;

a low pressure spool configured for rotation coaxially with respect to the combustor;

a high pressure spool configured for rotation coaxially with respect to the low pressure spool, wherein the high pressure spool has an annular drum having a portion radially outward from the combustor; and

a fan stage directly driven by the high pressure spool, wherein the fan stage has a plurality of fan blades extending from the annular drum.

28. A turbofan engine comprising:

an outer engine case through which gas flows from an upstream end to a downstream end, the outer engine case comprising;

a low pressure turbine vane array extending radially inward from the outer engine case near the downstream end;

an inner engine case disposed concentrically within the outer engine case, the inner engine case comprising;

a low pressure compressor vane array extending radially inward from the inner engine case;

a high pressure compressor vane array extending radially outward from the inner engine case downstream of the low pressure compressor vane array; and

a high pressure turbine vane array extending radially outward from the inner engine case downstream of the high pressure compressor vane array and upstream of the low pressure turbine vane array;

a combustor disposed between the high pressure compressor vane array and the high pressure turbine vane array;

a high pressure drum extending from an upstream end to a downstream end between the outer engine case and the inner engine case, the high pressure drum comprising;

a fan stage extending radially outward from the high pressure drum;

a high pressure compressor blade array extending radially inward from the high pressure drum to engage the high pressure compressor vane array; and

a high pressure turbine blade array extending radially inward from the high pressure drum to engage the high pressure turbine vane array;

a low pressure shaft extending from the upstream end to the downstream end within the inner engine case, the low pressure shaft comprising;

a low pressure compressor blade array extending radially outward from the low pressure shaft to engage the low pressure compressor vane array; and

an epicyclic gear system driven by the low pressure shaft; and

a low pressure compressor shaft driven by the planetary gear system, the low pressure compressor shaft comprising a low pressure compressor blade array extending radially outward from the low pressure compressor shaft to engage the low pressure compressor vane array.