Modular gas turbine engine

• US 4,934,140 A
• Filed: 05/13/1988
• Issued: 06/19/1990
• Est. Priority Date: 05/13/1988
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Monsarrat, William G., Dennison, William T., Brodell, Robert F.
• Primary Examiner(s): Stout, Donald E.
• Application Number:
  US07/193,473
• Time in Patent Office: 767 Days
• Field of Search: 60/226.1, 60/39.161, 60/39.31, 60/262, 244/54
• US Class Current: 60/226.1
• CPC Class Codes: F01D 7/00 Rotors with blades adjustable in operation; Control thereof for reversing F01D1/30
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type

Abstract

A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.

Claims

1. A gas turbine fan engine installation on an airplane pylon, the pylon including an annular cowl, struts extending inwardly from said cowl and having engine supports on the inner end,

an engine supported on said supports and defining between it and the cowl a path for fan air over said struts and around the engine,

engine attachment means securing said engine to said supports,

a fan including fan blades mounted on and driven by said engine and extending across said fan air path.

said engine including a compressor, a combustion section and a turbine, drive means for said fan including a reduction gear driven by said turbine and having a ring for supporting the fan blades,

means accessible from said air path for removing the individual fan blades from said ring,

means accessible from said air path for removing said attachment means for said engine to provide for removal of the entire engine axially from said cowl after removal of said fan blades and said attaching means.

2. An engine installation as in claim 1 in which the engine includes pitch changing means attached to said fan blades for changing the pitch thereof, and

means accessible from said air path for disengaging said pitch changing means to permit removal of the blades.

3. An installation as in claim 2 in which the engine includes a removable ring forming a part on the inner wall of the fan air path and in which the ring is removable by disengaging means accessible from the air path and in which the pitch changing mechanism attachment for the blades is accessible by removal of said ring.

4. An engine installation as in claim 1 in which a removably attached core cowl is attached by removable attachment means to the inner end of the struts and forms a part of the inner wall of the gas path extending rearwardly from said struts and in which the attachment means for said core cowl is accessible from said air path and in which removal of said cowl gives access to the engine attachment means, the engine rearwardly of said struts being smaller in diameter than the annulus defined by the inner ends of the struts for forward removal of the engine as an entirety through said annulus.

5. A gas turbine fan engine of the type adapted for installation on an airplane pylon having an annular cowl outwardly of the fan and struts extending inwardly from the cowl across the fan to core engine supports inwardly of the fan, wherein the improvement comprises:

a core engine having a forward section and a rearward section joined one to the other, each of the forward section and the rearward section being separable from the pylon independently of the other and without the necessity of removing the other from the airplane.

6. The invention according to claim 19 wherein the gas turbine fan engine has

a low pressure compressor casing and a rotor within said casing,

a fan including a ring and blades in the ring supported externally of said casing,

a main strut surrounding the engine and supporting the engine and having a sleeve forming a part of the inner wall of the fan air path,

a housing secured by first bolts to said main strut and extending inwardly to the downstream end of the compressor case and being bolted to said casing by bolts accessible rearwardly of said housing,

a core cowl secured to and extending downstream from said sleeve and removably secured thereto,

a first support structure extending across the compressor gas path at the downstream end of the low pressure compressor and having an inwardly extending element carrying at its inner end a bearing for the downstream end of the compressor rotor,

a second structure extending across the gas path forwardly of said first structure and having a bearing inwardly of the gas path on which said structure is rotatable,

a sleeve surrounding said second structure and connecting said structure to said fan ring, second bolts accessible from said fan air path holding said sleeve to said ring,

said low pressure compressor and the parts of the engine forwardly thereof being removable as a unit by release of said first bolts and said second bolts by access from the fan air path.

7. A gas turbine engine installation as in claim 6 in which said sleeve is surrounded by a cowl ring forming a part of the inner wall of the fan air path and secured to said fan ring by other bolts accessible from said fan air path, removal of these other bolts and the cowl ring permitting access to said second bolts.

8. A gas turbine engine installation as in claim 6 in which the low pressure compressor rotor at its downstream end is axially slideable within the bearing support structure.

9. A gas turbine engine installation as in claim 8 in which the compressor rotor and drive shaft are held in axial position by a threaded ring on the end of the shaft, and in which this ring is accessible from the front end of the engine.

10. A gas turbine engine installation as in claim 6 in which the compressor rotor at its downstream end is axially slideable within the bearing support structure and in which the rotor is driven by a drive shaft to which said rotor is connected by axially extending splines permitting the engine to be separated axially at this point.

11. A gas turbine engine installation as in claim 10 in which there is an impeller sleeve at the forward end of the engine with a removable cap on this sleeve for access centrally of the engine axially for a tool to reach said threaded ring.

12. A gas turbine fan engine as in claim 11 in which the gearbox and drive gear are separable after removal of the nose cowl by removal of the fan cowl and the bolts holding the ring gear to the sleeve 134.

13. A gas turbine fan engine as in claim 11 in which the connecting structure is supported by a bearing surrounding the gearbox, this bearing being smaller in diameter than the ring gear and in which the gearbox and gearing may be removed as a unit without the ring gear since the surrounding bearing permits axial sliding movement, and the bearing and gearbox can move out within the ring gear, the teeth on the ring gear permitting axial sliding movement.

14. A gas turbine fan engine as in claim 13 in which the impeller shaft carries a geared ring in mesh with a pinion on the scavenge and pressure pump shaft.

15. A gas turbine fan engine in claim 14 in which the removal of the first bolts releases the bearing for the fan engine from the compressor casing.

16. The invention according to claim 5 wherein the gas turbine fan engine has

a low pressure compressor including a rotor and casing,

a fan ring surrounding the casing having fan blades therein extending across the fan gas path,

supporting structure extending across the gas path at the inlet to the compressor,

a bearing for the fan rotor at the forward end of said supporting structure,

a gearbox secured by first bolts to said supporting structure,

a sun gear, planet gears in mesh therewith and mounted for rotation on said gearbox, and a ring gear in mesh with said planet gears and surrounding said planet gears,

a drive sleeve extending from said compressor rotor to said sun gear and having a spline connection with both for axially sliding movement,

a connecting structure connecting the fan ring to said ring gear and extending across the compressor gas path forwardly of the supporting structure and including,

a sleeve connecting said structure to said ring and being held by second bolts to both,

a fan cowl surrounding said sleeve and forming the forward end of the inner wall f the fan air path, said cowl being secured by bolts to the sleeve,

a nose cone including mechanism driven from said drive sleeve and including a housing secured to said gearbox by said third bolts,

a second drive sleeve connecting said mechanism to said first drive sleeve and splines on the end of said second sleeve to permit axial movement therebetween,

a nose cone cowl around said cone and secured by fourth bolts to the rearward end of said cone, said bolts being accessible from the fan gas path externally of said cowl, and

said nose cowl being removable from said gearbox by removal of the third bolts holding the nose cone to said gearbox, the first bolts being accessible by removal of the nose cowl and said housing.

17. A gas turbine fan engine installation as in claim 16 in which the splines on the drive sleeve from the compressor rotor to the sun gear permit axial sliding movement at this point for forward movement of the gearbox in separating the parts.

18. The invention according to claim 5 wherein the gas turbine fan engine has a nose cowl with a lubricant system therein including a housing, scavenge and pressure lubricant pumps in the housing, an air oil cooler for the lubricant, an impeller for causing cooling air flow through the air oil cooler, a nose cone cowl for the cone having an air inlet connection to the duct connecting to the said impeller, the latter having a surrounding case, a sleeve supporting the impeller and having a removable threaded cap at its forward end, drive means for said impeller extending rearwardly from said housing, drive means for said impeller being splined thereto for axial separation, bolts securing said cowl to said housing at the rearward end of said cowl, said bolts being accessible externally of said cowl, said inlet ducts having an axially sliding connection to said impeller case and said cowl having an axially slideable connection to said housing at the rearward end of said shield, supporting structure for said housing located rearwardly of said housing and second bolts securing said housing to said structure, said second bolts being accessible from within the cowl upon removal of the cowl whereby the entire nose cone with its associated structure therein is removable as a unit from the supporting structure to which it is secured.

19. The invention according to claim 5 wherein the gas turbine fan engine has a low pressure compressor case, a compressor rotor within the case and a fan ring surrounding said case, a bearing secured by first bolts to said case and on which the ring is supported for rotation, a surrounding cowl ring, struts extending inwardly from said ring and defining a fan air path, supports on the inner ends of the struts for the engine, a housing extending inwardly from the supports to the low pressure compressor casing and secured thereto by said first bolts, fan blades secured to said ring and being rotatable on their own axes for pitch changing, each blade having an arm on its inner end,

pitch changing mechanism for said blades including an actuator secured to said mounts, a sleeve supported by said housing and axially movable by said actuators to which it is pinned, a second sleeve mounted for rotation on said first sleeve and also guided by said housing for axial movement, a thrust bearing between said sleeves to cause them to move axially in unison, links connecting said second sleeve to said fan arms, a strut extending across the compressor gas path at the forward end of the compressor and having a support inwardly of the path for a bearing for the compressor rotor, a reduction gear drive for said fan forward of the compressor, a connecting structure from said drive to said fan ring, said structure carrying a ring gear at its inner end and extending across the gas path, the outer end of said structure being secured by second bolts to said ring, said fan and actuating mechanism being removable as a unit from its position around the compressor after the latter is removed from the rest of the engine by removal of said second bolts, the actuators being previously disconnected from said first sleeve by removal of the connecting pins before removal of the low pressure compressor and associated structure from the remainder of the installation.

20. The invention according to claim 5 wherein the gas turbine fan engine has a low pressure compressor and a high pressure compressor, wherein the forward section of the engine comprises the low pressure compressor and components forward thereof and wherein the rearward section of the engine comprises the high pressure compressor and components rearward thereof.

21. The invention according to claim 20 wherein the forward section and the rearward section are separable on from the other at bolts joining the low pressure compressor to the high pressure compressor and at a spline joining the rotor of the low pressure compressor to a shaft extending forwardly through the center of the high compressor.

22. The invention according to claim 5 which further includes a fan rotor and pitch changing mechanism mounted within a housing attached to the core engine supports and wherein the forward section and the rearward section of the engine are attached onto the other at said housing.

23. The invention according to claim 22 wherein the fan rotor and the pitch changing mechanism are separable from the pylon with the forward section.