WO2014074145A1 - Angled core gas turbine engine mounting - Google Patents

Angled core gas turbine engine mounting Download PDF

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Publication number
WO2014074145A1
WO2014074145A1 PCT/US2013/031197 US2013031197W WO2014074145A1 WO 2014074145 A1 WO2014074145 A1 WO 2014074145A1 US 2013031197 W US2013031197 W US 2013031197W WO 2014074145 A1 WO2014074145 A1 WO 2014074145A1
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WO
WIPO (PCT)
Prior art keywords
engine
axis
propulsor
core
aircraft
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.)
Ceased
Application number
PCT/US2013/031197
Other languages
French (fr)
Inventor
Gabriel L. Suciu
Jesse M. Chandler
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Priority to US14/440,698 priority Critical patent/US10001063B2/en
Publication of WO2014074145A1 publication Critical patent/WO2014074145A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • Conventional aircraft architecture includes wing mounted gas turbine engines.
  • gas turbine engines are mounted atop the fuselage or on opposite sides of the aircraft fuselage.
  • gas turbine engines that in include a fan section driven by an engine core or gas generator.
  • the engine core includes a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section through a driven shaft.
  • Alternate aircraft architectures may require alternate mounting locations of the gas turbine engines to enable specific wing and fuselage configurations.
  • conventional gas turbine engine configurations have been developed to operate with conventional aircraft architectures.
  • a propulsion system for an aircraft includes a first turbine engine including a first engine core that drives a first propulsor.
  • the first propulsor is disposed about a first propulsor axis and the first engine core is disposed about a first core axis that is skewed from the first propulsor axis.
  • a second turbine engine includes a second engine core that drives a second propulsor.
  • the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis.
  • Tthe second engine core is disposed about a second core axis that is skewed from the one or both of the first propulsor axis and the second core axis.
  • first core axis and the second core axis are angled away from each other.
  • the first core axis is disposed at an angle greater than ninety (90) degrees relative to the second core axis.
  • first core axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
  • a burst zone is defined about each of the first and second engine cores.
  • each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
  • the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
  • the burst angle is at least about +/- fifteen (15) degrees.
  • the first and second engine cores include a reverse flow gas turbine engine.
  • An aircraft includes a fuselage, and a first turbine engine including a first engine core that drives a first propulsor.
  • the first propulsor is disposed about a first propulsor axis.
  • a second turbine engine includes a second engine core and a second propulsor.
  • the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis.
  • the first engine core and the second engine core are mounted at an angle relative a corresponding one of the first and second propulsor axes.
  • the first engine core is disposed about a first engine axis and the second engine core is disposed about a second engine axis.
  • the first engine axis and the second engine axis are angled away from each other.
  • the first engine axis is disposed at an angle greater than ninety (90) degrees relative to the second engine axis.
  • first engine axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
  • a burst zone is defined about each of the first and second engine cores.
  • each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
  • the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
  • the burst angle is at least about +/- fifteen (15) degrees.
  • the first and second engine cores include a reverse flow gas turbine engine.
  • Figure 1 is a schematic view of an aircraft including a propulsion system mounted within the fuselage.
  • Figure 2 is a schematic view of the example propulsion system.
  • Figure 3 is a schematic view of a burst zone defined about the example propulsion system.
  • an aircraft 10 includes a fuselage 12 having wings 16 and a tail 14.
  • a propulsion system 18 is mounted aft end of the fuselage 12.
  • the propulsion system 18 includes first and second engine cores 20a-b, which are reverse core gas turbine engines that drive corresponding first and second propulsors that include respective fan sections 22a-b.
  • the first and second fan sections 22a-b provide the propulsive thrust of the disclosed propulsion system.
  • Each of the fan sections 22a-b are disposed about corresponding first and second propulsor axis Al and A2.
  • the first and second engine cores 20a-b is disposed about a corresponding first and second engine axes Bl and B2. That is the first engine core 20a is disposed about the first engine axis B 1 and drives the first propulsor about the first propulsor axis Al.
  • the second engine core 20b is disposed about the second engine axis B2 and drives the second fan section 20b about the second propulsor axis A2.
  • the illustrated reverse engine cores 20a-b are gas generators that include a compressor 24, a combustor 26 and a turbine 28. Air is drawn in through inlets 32a-b to the compressor 24 is compressed and communicated to a combustor 26. In the combustor 26, air is mixed with fuel and ignited to generate an exhaust gas stream that expands through the turbine 28 where energy is extracted and utilized to drive the compressor 24 and corresponding fan 22a-b. In this example the engine cores 20a-b drive the corresponding fan 22a-b through a geared architecture 30a-b.
  • each of the first and second fans 22a-b and related gearing 30a-b is mounted substantially parallel to each other about respective propulsor axes Al, A2.
  • the first and second engine axes Bl, B2 are disposed at an angle 34 relative to the corresponding propulsor axis Al, A2.
  • the angle 34 is greater than about thirty (30) degrees. As appreciated other angles are within the contemplation of this disclosure.
  • gas turbine engines are not typically mounted next to each other due to practical limitations related to overall aircraft survivability in the event of engine failure.
  • a burst zone is defined between gas turbine engines within which another gas turbine engine is not permitted due to possible fragmentation from one failed engine disabling the second engine.
  • the disclosed engine cores 20a-b are disposed at the angle 34 relative to the corresponding propulsor axes Al and A2 and to each other such that neither engine core 20a-b is disposed within a burst zone 36a-b of the other engine core 20a-b.
  • each of the engine cores 20a-b is disposed at an angle away from the other engine core 20a-b such that each is orientated outside of the others bust zone 36a-b.
  • the engine cores 20a-b are angled away from each other at an angle 42 ( Figure 2).
  • the angle 42 is greater than about ninety (90) degrees.
  • other angles 42 could be utilized depending on the definition of respective burst zones 36a-b.
  • the respective bust zones 36a-b is defined as respective annular regions about the corresponding engine core 20a-b.
  • the annular region is disposed at an angle 38 outward from a line 40 perpendicular to the engine axis Bl, B2.
  • the example angle is at least fifteen (15) degrees and is determined based on application specific considerations.
  • airframe regulations may also define an angular span of the burst zones 36a-b and thereby the angle 38.
  • the relative orientation between the first and second engine cores 20a-b defines the corresponding bust zones 36a-b that does not interfere with the other engine core 20a-b to comply with application specific survivability requirements.
  • gas generators are mounted in a configuration placing each outside of the others burst zone, fuselage and substantially adjacent mounted propulsors are feasible within desired limitations.
  • the side by side adjacent mounting configuration further enables alternate aircraft architectures.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Retarders (AREA)
  • Laminated Bodies (AREA)

Abstract

A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.

Description

ANGLED CORE GAS TURBINE ENGINE MOUNTING
CROSS REFERENCE TO RELATED APPLICATION
[0001] This application claims priority to United States Provisional Application No. 61/725,099 filed on November 12, 2012.
BACKGROUND
[0002] Conventional aircraft architecture includes wing mounted gas turbine engines. In some aircraft architectures gas turbine engines are mounted atop the fuselage or on opposite sides of the aircraft fuselage.
[0003] Commercial aircraft typically utilize gas turbine engines that in include a fan section driven by an engine core or gas generator. The engine core includes a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section through a driven shaft.
[0004] Alternate aircraft architectures may require alternate mounting locations of the gas turbine engines to enable specific wing and fuselage configurations. However, conventional gas turbine engine configurations have been developed to operate with conventional aircraft architectures.
[0005] Accordingly, alternate gas turbine engine configurations may be required and developed to enable implementation of favorable aspects of alternate engine architectures.
SUMMARY
[0006] A propulsion system for an aircraft according to an exemplary embodiment of this disclosure, among other possible things includes a first turbine engine including a first engine core that drives a first propulsor. The first propulsor is disposed about a first propulsor axis and the first engine core is disposed about a first core axis that is skewed from the first propulsor axis. A second turbine engine includes a second engine core that drives a second propulsor. The second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis. Tthe second engine core is disposed about a second core axis that is skewed from the one or both of the first propulsor axis and the second core axis.
[0007] In a further embodiment of the foregoing aircraft, the first core axis and the second core axis are angled away from each other.
[0008] In a further embodiment of any of the foregoing aircrafts, the first core axis is disposed at an angle greater than ninety (90) degrees relative to the second core axis.
[0009] In a further embodiment of any of the foregoing aircrafts, the first core axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
[0010] In a further embodiment of any of the foregoing aircrafts, a burst zone is defined about each of the first and second engine cores.
[0011] In a further embodiment of any of the foregoing aircrafts, each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
[0012] In a further embodiment of any of the foregoing aircrafts, the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
[0013] In a further embodiment of any of the foregoing aircrafts, the burst angle is at least about +/- fifteen (15) degrees.
[0014] In a further embodiment of any of the foregoing aircrafts, the first and second engine cores include a reverse flow gas turbine engine.
[0015] An aircraft according to an exemplary embodiment of this disclosure, among other possible things includes a fuselage, and a first turbine engine including a first engine core that drives a first propulsor. The first propulsor is disposed about a first propulsor axis. A second turbine engine includes a second engine core and a second propulsor. The second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative a corresponding one of the first and second propulsor axes.
[0016] In a further embodiment of the foregoing aircraft, the first engine core is disposed about a first engine axis and the second engine core is disposed about a second engine axis. The first engine axis and the second engine axis are angled away from each other.
[0017] In a further embodiment of any of the foregoing aircrafts, the first engine axis is disposed at an angle greater than ninety (90) degrees relative to the second engine axis.
[0018] In a further embodiment of any of the foregoing aircrafts, the first engine axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
[0019] In a further embodiment of any of the foregoing aircrafts, a burst zone is defined about each of the first and second engine cores.
[0020] In a further embodiment of any of the foregoing aircrafts, each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
[0021] In a further embodiment of any of the foregoing aircrafts, the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
[0022] In a further embodiment of any of the foregoing aircrafts, the burst angle is at least about +/- fifteen (15) degrees.
[0023] In a further embodiment of any of the foregoing aircrafts, the first and second engine cores include a reverse flow gas turbine engine.
[0024] Although the different examples have the specific components shown in the illustrations, embodiments of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
[0025] These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] Figure 1 is a schematic view of an aircraft including a propulsion system mounted within the fuselage.
[0027] Figure 2 is a schematic view of the example propulsion system. [0028] Figure 3 is a schematic view of a burst zone defined about the example propulsion system.
DETAILED DESCRIPTION
[0001] Referring to the Figures 1 and 2 an aircraft 10 includes a fuselage 12 having wings 16 and a tail 14. A propulsion system 18 is mounted aft end of the fuselage 12. The propulsion system 18 includes first and second engine cores 20a-b, which are reverse core gas turbine engines that drive corresponding first and second propulsors that include respective fan sections 22a-b. The first and second fan sections 22a-b provide the propulsive thrust of the disclosed propulsion system.
[0002] Each of the fan sections 22a-b are disposed about corresponding first and second propulsor axis Al and A2. The first and second engine cores 20a-b is disposed about a corresponding first and second engine axes Bl and B2. That is the first engine core 20a is disposed about the first engine axis B 1 and drives the first propulsor about the first propulsor axis Al. The second engine core 20b is disposed about the second engine axis B2 and drives the second fan section 20b about the second propulsor axis A2.
[0003] The illustrated reverse engine cores 20a-b are gas generators that include a compressor 24, a combustor 26 and a turbine 28. Air is drawn in through inlets 32a-b to the compressor 24 is compressed and communicated to a combustor 26. In the combustor 26, air is mixed with fuel and ignited to generate an exhaust gas stream that expands through the turbine 28 where energy is extracted and utilized to drive the compressor 24 and corresponding fan 22a-b. In this example the engine cores 20a-b drive the corresponding fan 22a-b through a geared architecture 30a-b.
[0004] In the disclosed example, each of the first and second fans 22a-b and related gearing 30a-b is mounted substantially parallel to each other about respective propulsor axes Al, A2. The first and second engine axes Bl, B2 are disposed at an angle 34 relative to the corresponding propulsor axis Al, A2. In this example the angle 34 is greater than about thirty (30) degrees. As appreciated other angles are within the contemplation of this disclosure.
[0005] Referring to Figure 3, with continued reference to Figure 2, gas turbine engines are not typically mounted next to each other due to practical limitations related to overall aircraft survivability in the event of engine failure. A burst zone is defined between gas turbine engines within which another gas turbine engine is not permitted due to possible fragmentation from one failed engine disabling the second engine.
[0006] The disclosed engine cores 20a-b are disposed at the angle 34 relative to the corresponding propulsor axes Al and A2 and to each other such that neither engine core 20a-b is disposed within a burst zone 36a-b of the other engine core 20a-b. In other words, each of the engine cores 20a-b is disposed at an angle away from the other engine core 20a-b such that each is orientated outside of the others bust zone 36a-b. In this example, the engine cores 20a-b are angled away from each other at an angle 42 (Figure 2). In this example, the angle 42 is greater than about ninety (90) degrees. As appreciated other angles 42 could be utilized depending on the definition of respective burst zones 36a-b.
[0007] The respective bust zones 36a-b is defined as respective annular regions about the corresponding engine core 20a-b. In this example the annular region is disposed at an angle 38 outward from a line 40 perpendicular to the engine axis Bl, B2. The example angle is at least fifteen (15) degrees and is determined based on application specific considerations. Moreover, airframe regulations may also define an angular span of the burst zones 36a-b and thereby the angle 38.
[0008] The relative orientation between the first and second engine cores 20a-b defines the corresponding bust zones 36a-b that does not interfere with the other engine core 20a-b to comply with application specific survivability requirements.
[0009] Accordingly, because the gas generators are mounted in a configuration placing each outside of the others burst zone, fuselage and substantially adjacent mounted propulsors are feasible within desired limitations. The side by side adjacent mounting configuration further enables alternate aircraft architectures.
[0010] Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and content of this disclosure.

Claims

CLAIMS What is claimed is:
1. A propulsion system for an aircraft comprising:
a first turbine engine including a first engine core that drives a first propulsor, wherein the first propulsor is disposed about a first propulsor axis and the first engine core is disposed about a first core axis that is skewed from the first propulsor axis; and
a second turbine engine including a second engine core that drives a second propulsor, wherein the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis, and the second engine core is disposed about a second core axis that is skewed from the one or both of the first propulsor axis and the second core axis.
2. The aircraft as recited in claim 1, wherein the first core axis and the second core axis are angled away from each other.
3. The aircraft as recited in claim 2, wherein the first core axis is disposed at an angle greater than ninety (90) degrees relative to the second core axis.
4. The aircraft as recited in claim 2, wherein the first core axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
5. The aircraft as recited in claim 2, wherein a burst zone is defined about each of the first and second engine cores.
6. The aircraft as recited in claim 5, wherein each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
7. The aircraft as recited in claim 5, wherein the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
8. The aircraft as recited in claim 7, wherein the burst angle is at least about +/- fifteen (15) degrees.
9. The aircraft as recited in claim 1, wherein the first and second engine cores comprise a reverse flow gas turbine engine.
10. An aircraft comprising;
a fuselage;
a first turbine engine including a first engine core that drives a first propulsor, wherein the first propulsor is disposed about a first propulsor axis; and
a second turbine engine including a second engine core and a second propulsor, wherein the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis, and the first engine core and the second engine core are mounted at an angle relative a corresponding one of the first and second propulsor axes.
11. The aircraft as recited in claim 10, wherein the first engine core is disposed about a first engine axis and the second engine core is disposed about a second engine axis, wherein the first engine axis and the second engine axis are angled away from each other.
12. The aircraft as recited in claim 11, wherein the first engine axis is disposed at an angle greater than ninety (90) degrees relative to the second engine axis.
13. The aircraft as recited in claim 11, wherein the first engine axis and second engine axis are disposed at an angle greater than about thirty (30) degrees relative to the corresponding first and second propulsor axes.
14. The aircraft as recited in claim 11, wherein a burst zone is defined about each of the first and second engine cores.
15. The aircraft as recited in claim 14, wherein each of the first and second engine cores is disposed outside of a burst zone defined about the other of the first and second engine cores.
16. The aircraft as recited in claim 14, wherein the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.
17. The aircraft as recited in claim 16, wherein the burst angle is at least about +/- fifteen (15) degrees.
18. The aircraft as recited in claim 10, wherein the first and second engine cores comprise a reverse flow gas turbine engine.
PCT/US2013/031197 2012-11-12 2013-03-14 Angled core gas turbine engine mounting Ceased WO2014074145A1 (en)

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US201261725099P 2012-11-12 2012-11-12
US61/725,099 2012-11-12

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