GB2526609A - Compressor drum - Google Patents

Compressor drum Download PDF

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Publication number
GB2526609A
GB2526609A GB1409589.7A GB201409589A GB2526609A GB 2526609 A GB2526609 A GB 2526609A GB 201409589 A GB201409589 A GB 201409589A GB 2526609 A GB2526609 A GB 2526609A
Authority
GB
United Kingdom
Prior art keywords
compressor
annular support
annular
compressor drum
reinforcing element
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB1409589.7A
Other versions
GB201409589D0 (en
Inventor
Adam Stapleton
John Pursell
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1409589.7A priority Critical patent/GB2526609A/en
Publication of GB201409589D0 publication Critical patent/GB201409589D0/en
Publication of GB2526609A publication Critical patent/GB2526609A/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A compressor drum 31, for an axial-flow compressor, comprising; annular supports 25, 25, and 25, which are rotatable about a rotational axis. The annular supports have radially inner rims 35, 35, and 35, defining axial bores r1, r2, and r3, through which the rotational axis extends, and radially outer rims 37, 37, and 37, supporting a plurality of compressor blades 26. The annular support comprises at least one circumferentially extending reinforcing element 39. A second embodiment provides a compressor drum with an upstream annular support 25 or 25 and a downstream annular support 25. The radius of the axial bore of the upstream annular support r1 or r2 should be greater than r3 of the downstream annular support. The reinforcing element may be formed of a metal matrix composite (MMC) or titanium or titanium alloy. The second embodiment reduces pooling of oil and engine fluids in the annular cavities (see 29 prior art figure 2) and allows for fewer fluid drain holes 30 to minimise areas of stress concentration.

Description

COMPRESSOR DRUM
Field of the Invention
The present invention relates to an axial-flow compressor, and, more particularly, to an axial-flow compressor for a gas turbine engine.
Background of the Invention
With reference to Figure 1, a ducted fan gas turbine engine is generally indicated at 10 and has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
As shown in Figure 2, the high and intermediate pressure compressors 14, 13 typically comprise a compressor drum having a series of annular supports 25 bearing compressor blades 26 (which may be mounted on or integral with the support/disc). The supports are rotatably driven within a casing 27. Axially interspaced between the compressor blades are stator vanes 28 depending from the inner wall of the casing.
The annular supports are axially spaced from one another by a series of annular cavities 29.
There is a tendency for oil and other engine fluids to collect in these cavities and therefore it is known to provide fluid drain holes 30 in the compressor drum to allow fluids to escape.
The stresses on the compressor drum are high during use and the presence of these fluid drain holes results in stress concentrations which can lead to component failure.
Furthermore, fluid drain holes increase manufacturing costs and reduce compressor efficiency by allowing escape of high pressure air.
There is a need for an axial-flow compressor drum that reduces the pooling of oil and other engine fluids whilst minimising areas of stress concentration.
Summary of the Invention
In a first aspect, the present invention provides a compressor drum for an axial-flow compressor, the compressor drum comprising at least one annular support which is rotatable about a rotational axis, the annular support having a radially inner rim defining an axial bore through which the rotational axis extends, and a radially outer rim supporting a plurality of compressor blades, wherein the annular support comprises at least one circumferentially extending reinforcing element.
The circumferentially extending reinforcing element helps carry the load of the compressor blades on the radially outer rim of the annular support thus facilitating a reduction in the radial extension of the annular support (i.e. the distance between the radially inner and radially outer rims) and a corresponding increase in the size of the axial bore. The increase in the size of the axial bore allows fluid communication between the annular cavities within the compressor drum and therefore pooling of oil and other engine fluids can be reduced.
Accordingly, the number of fluid drain holes (and thus the areas of stress concentration) can also be reduced. Furthermore, the reduced radial extension allows a reduction in the amount of material used to form the annular support. This has weight benefits. The reduced radial extension also reduces thermal discrepancies between the inner and outer rims so that the annular support can expand and contract at a similar rate to the casing surrounding the compressor drum.
Optional features of the invention will now be set out. These are applicable singly or in any combination with any aspect of the invention.
The circumferentially extending reinforcing element may be an annular reinforcing element.
The circumferentially extending reinforcing element(s) may be provided within the annular support e.g. embedded, inserted or encased within the material forming the annular support.
In some embodiments, the circumferentially extending reinforcing element is formed of a different material to that forming the annular support. In some embodiments, the or each reinforcing element is formed of a metal matrix composite (MMC) e.g. a titanium/titanium alloy MMC.
In some embodiments, the annular support is formed of titanium or a titanium alloy.
In some embodiments, the circumferentially extending reinforcing element(s) extend(s) from proximal the radially inner rim to proximal the radially outer rim.
In some embodiments, the reinforcing element is inserted into a groove (e.g. a machined groove) on the annular support. The groove may subsequently be sealed e.g. with titanium or titanium alloy. Hot isotactic pressing may be used to seal with the groove with powdered metal (e.g. titanium/titanium alloy) by diffusion bonding.
The compressor blades on the annual support may be integral with the radially outer rim such that the annular support is a bladed ring (or bling).
In some embodiments, the compressor drum comprises a plurality of annular supports each having at least one circumferentially extending reinforcing element.
Two or more of the plurality of annular supports having at least one circumferentially extending reinforcing element may be provided axially adjacent to one another.
Axially adjacent annular supports may be integrally formed. For example, they may be integrally joined through their radially outer rims or the radially inner rim of one annular support (e.g. a downstream annular support) may be integrally joined to the radially outer rim of the axially adjacent annular support (e.g. an upstream annular support).
In a second aspect, the present invention provides a compressor drum for an axial-flow compressor, the compressor drum comprising an upstream annular support and a downstream annular support, said annular supports being rotatable about a rotational axis, each annular support having a radially inner rim defining an axial bore through which the rotational axis extends, and a radially outer rim supporting a plurality of respective compressor blades, wherein the axial bore of the upstream annular support has a greater radius than axial bore of the downstream annular support.
By providing an upstream annular support with an increased axial bore, fluid communication between the annular cavities (defined by the annular supports) within the compressor drum is possible and therefore pooling of oil and other engine fluids can be reduced. Accordingly, the number of fluid drain holes (and thus the areas of stress concentration) can also be reduced. Furthermore, the upstream annular support with the increased axial bore will have a reduced radial extension and thus will be formed of a reduced amount of material. This has cost and weight benefits. The reduced radial extension also reduces thermal discrepancies between the inner and outer rims so that the upstream annular support can expand and contract at a similar rate to the casing surrounding the compressor drum.
The compressor blades on the downstream annular support may be integral with the radially outer rim such that the downstream annular support is a bladed disk (or blisk).
The compressor blades on the upstream annual support may be integral with the radially outer rim such that the upstream annular support is a bladed ring (or bling).
In some embodiments, the compressor drum comprises a plurality of upstream annular supports each having an increased axial bore/reduced radial extension. Two or more of the plurality of upstream annular supports having an increased axial bore/reduced radial extension may be provided axially adjacent to one another.
Axially adjacent annular supports (e.g. axially adjacent upstream annular supports or an upstream support and an axially adjacent downstream support) may be integrally formed.
For example, they may be integrally joined through their radially outer rims or the radially inner rim of one annular support may be integrally joined to the radially outer rim of the axially adjacent annular support.
In some embodiments, the or each upstream annular support may comprise at least one circumferentially extending reinforcing element. The circumferentially extending reinforcing agent may be an annular reinforcing element.
The or each circumferentially extending reinforcing element may be provided within the respective annular support e.g. embedded, inserted or encased within the material forming the annular support.
The reinforcing element helps carry the load of the compressor blades on the radially outer rim of the or each upstream annular support thus facilitating the reduction in the radial extension of the annular support and the corresponding increase in the size of the axial bore.
In some embodiments, the or each circumferentially extending reinforcing element is formed of a different material to that forming the upstream annular supports. In some embodiments, the or each reinforcing element is formed of a metal matrix composite (MMC) e.g. a titanium/titanium alloy MMC.
In some embodiments, the annular supports aie formed of titanium or a titanium alloy.
In some embodiments, the circumferentially extending reinforcing element(s) extend(s) from proximal the radially inner rim to proximal the radially outer rim of the respective upstream annular support.
In some embodiments, the reinforcing element is inserted into a groove (e.g. a machined groove) on the annular support. The groove may subsequently be sealed e.g. with titanium or titanium alloy. Hot isotactic pressing may be used to seal with the groove with powdered metal (e.g. titanium/titanium alloy) by diffusion bonding.
The terms "upstream" and "downstream" are intended to refer to the direction of air flow through the compressor with air flowing from upstream to downstream.
In a third aspect, the present invention provides an axial flow compressor having a compressor drum according to the first or second aspect.
The compressor drum is enclosed within a casing. A series of axially spaced pluralities of stator vanes are provided depending from the inner surface of the casing, one plurality of stator vanes interposed between each plurality of compressor blades.
In a fourth aspect, the present invention provides a gas turbine engine having a compressor according to the third aspect.
Brief Description of the Drawings
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which: Figure 1 shows a ducted fan gas turbine engine; Figure 2 shows an axial cross-section through a known compressor drum; and Figure 3 shows an axial cross-section through a compressor drum according to a first embodiment of the present invention.
Detailed Description and Further Optional Features of the Invention A first embodiment of the present invention is shown in Figure 3. A compressor drum 31 comprises a first (upstream) annular support 25', a second (upstream) annular support 25" and a third (downstream) annular support 25. The first and second (upstream) annular supports 25, 25' are axially adjacent.
The annular supports are rotatable about a rotational axis, Y-Y.
Each annular support has a radially inner rim 35, 35', 35" defining an axial bore through which the rotational axis Y-Y extends, and a radially outer rim 37, 37', 37' supporting a plurality of respective compressor blades 26.
The axial bores of the first and second (upstream) annular supports 25', 25" have a greater radius ri, r2 than the radius r3 of the axial bore 36 of the downstream annular support 25.
By providing first and second (upstream) annular supports 25', 25" with an increased axial bore, fluid communication between the annular cavities 29 within the compressor drum 31 is possible and therefore pooling of oil and other engine fluids can be reduced. Accordingly, the number of fluid drain holes (and thus the areas of stress concentration) can also be reduced. Fuithermore, the first and second (upstream) annular supports 25, 25" with increased axial bores have a reduced radial extension and thus will be formed of a reduced amount of material. This has cost and weight benefits.
The reduced radial extension also reduces thermal discrepancies between the radially inner rim 35', 35" and radially outer rims 37', 37" so that the first and second (upstream) annular supports 25, 25" can expand and contract at a similar rate to the casing 27 surrounding the compressor drum 31.
The compressor blades 26 on the third (downstream) annular support 25" are integral with the radially outer rim 37 such that the third (downstream) annular support 25" is a bladed disk (or blisk).
The compressor blades 26 on the first and second (upstream) annual supports 25', 25" are integral with the respective radially outer rim 35', 35" such that the first and second (upstream) annular supports 25', 25" are bladed rings (or blings).
Each of the first and second (upstream) annular support 25', 25" comprises a respective annular reinforcing element 39 formed of a metal matrix composite comprising titanium/titanium alloy which is encased within the annular support 25', 25".
The annular reinforcing elements 39 help carry the load of the compressor blades 26 on the radially outer rims 37', 37" of the first and second (upstream) annular supports 25', 25" thus facilitating the reduction in the radial extension of the annular supports and the corresponding increase in the size of the axial bore 36', 36".
During manufacturing, the first and second (upstream) annular supports 25', 25" are each machined to provide a groove and the respective annular reinforcing element 39 is inserted into the groove. Each groove is subsequently be sealed with titanium or titanium alloy using hot isotactic pressing to effect diffusion bonding of powdered titanium/titanium alloy.
Each plurality of compressor blades 26 is spaced by a plurality of stator vanes 28 which depend from the casing 27.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
All references referred to above are hereby incorporated by reference.

Claims (16)

  1. CLAIMS1. A compressor drum for an axial-flow compressor, the compressor drum comprising at least one annular support which is rotatable about a rotational axis, the annular support having a radially inner rim defining an axial bore through which the rotational axis extends, and a radially outer rim supporting a plurality of compressor blades, wherein the annular support comprises at least one circumferentially extending reinforcing element.
  2. 2. A compressor drum according to claim 1 comprising a plurality of annular supports each having at least one circumferentially extending reinforcing element.
  3. 3. A compressor drum according to claim 2 wherein two or more of the plurality of annular supports having at least one circumferentially extending reinforcing element may be provided axially adjacent to one another.
  4. 4. A compressor drum according to claim 3 wherein axially adjacent annular supports are integrally formed.
  5. 5. A compressor drum for an axial-flow compressor, the compressor drum comprising an upstream annular support and a downstream annular support, said annular supports being rotatable about a rotational axis, each annular support having a radially inner rim defining an axial bore through which the rotational axis extends, and a radially outer rim supporting a plurality of respective compressor blades, wherein the axial bore of the upstream annular support has a greater radius than axial bore of the downstream annular support.
  6. 6. A compressor drum according to claim 5 comprising a plurality of upstream annular supports.
  7. 7. A compressor drum according to claim 6 wherein two or more of the plurality of upstream annular supports are axially adjacent to one another.
  8. 8. A compressor drum according to any one of claims 5 to 7 wherein the or each upstream annular support comprises at least one circumferentially extending reinforcing element.
  9. 9. A compressor drum according to any one of claims 1 to 4 and 8 wherein the or each circumferentially extending reinforcing element is an annular reinforcing element.
  10. 10. A compressor drum according to any one of claims 1 to 4, 8 or 9 wherein the or each circumferentially extending reinforcing element is embedded or inserted within the respective annular support.
  11. 11. A compressor drum according to any one of claims 1 to 4 or 8 to 10 wherein the or each circumferentially extending reinforcing element is formed of a metal matrix composite (MMC).
  12. 12. A compressor drum according to claim 11 wherein the metal matrix composite comprises titanium/titanium alloy.
  13. 13. An axial flow compressor having a compressor drum according to any one of claims lto2.
  14. 14. A gas turbine engine having a compressor according to claim 13.
  15. 15. A compressor drum substantially as any one embodiment herein described with reference to Figure 3.
  16. 16. An axial flow compressor substantially as any one embodiment herein described with reference to Figure 3.
GB1409589.7A 2014-05-30 2014-05-30 Compressor drum Withdrawn GB2526609A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1409589.7A GB2526609A (en) 2014-05-30 2014-05-30 Compressor drum

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1409589.7A GB2526609A (en) 2014-05-30 2014-05-30 Compressor drum

Publications (2)

Publication Number Publication Date
GB201409589D0 GB201409589D0 (en) 2014-07-16
GB2526609A true GB2526609A (en) 2015-12-02

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Family Applications (1)

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GB1409589.7A Withdrawn GB2526609A (en) 2014-05-30 2014-05-30 Compressor drum

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966523A (en) * 1975-08-11 1976-06-29 United Technologies Corporation Method of making filament reinforced composite rings from plural flat filamentary spiral layers
US5470524A (en) * 1993-06-15 1995-11-28 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Method for manufacturing a blade ring for drum-shaped rotors of turbomachinery
US20030233822A1 (en) * 2002-04-25 2003-12-25 Guenter Albrecht Compressor in a multi-stage axial form of construction
GB2456637A (en) * 1997-06-03 2009-07-29 Rolls Royce Plc A fibre reinforced metal rotor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966523A (en) * 1975-08-11 1976-06-29 United Technologies Corporation Method of making filament reinforced composite rings from plural flat filamentary spiral layers
US5470524A (en) * 1993-06-15 1995-11-28 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Method for manufacturing a blade ring for drum-shaped rotors of turbomachinery
GB2456637A (en) * 1997-06-03 2009-07-29 Rolls Royce Plc A fibre reinforced metal rotor
US20030233822A1 (en) * 2002-04-25 2003-12-25 Guenter Albrecht Compressor in a multi-stage axial form of construction

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Publication number Publication date
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