Mid turbine frame including a sealed torque box

Abstract

A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

Claims

1. A mid-turbine frame for a gas turbine engine comprising: an inner frame case defining a sealed torque box cavity; a plurality of spokes protruding radially outward from the inner frame case, each of said spokes including a cooling passage extending from a radially outward end of the spoke toward the inner frame case, wherein the cooling passage is sealed at a joint between the inner frame case and the spoke such that fluid transfer into said torque box at said joint is minimized; and at least one service line connected to the inner frame case.

2. The mid-turbine frame of claim 1, wherein each of said spokes comprises a cooling passage extending from a radially outward end of the spoke partially toward said inner frame case.

3. The mid-turbine frame of claim 2, wherein each of said spokes further comprises a redirection tube directing cooling fluid flowing through said cooling passage aft such that said cooling fluid bypasses the torque box.

4. The mid-turbine frame of claim 1, wherein said at least one service line is connected to the inner frame case via a connection feature, the connection feature interfacing the service line with a corresponding bearing support passage in the torque box.

5. The mid-turbine frame of claim 4, wherein the connection feature includes: a flange portion and an extension portion, the extension portion extending radially into said bearing support passage; a seal plate radially outward of said flange portion; and a seal element sealing said seal plate to said inner frame case.

6. The mid-turbine frame of claim 5, wherein the seal element sealing said seal plate to said inner frame case is a piston seal.

7. The mid-turbine frame of claim 5, further comprising a service line seal disposed between an outward facing surface of said extension portion and an inward facing surface of said bearing support passage.

8. The mid-turbine frame of claim 4, wherein said bearing support passage includes at least a first opening for providing fluid from said bearing support passage to a component disposed radially inward of the mid-turbine frame.

9. The mid-turbine frame of claim 1, wherein the inner frame case is configured such that all cooling air provided to an engine segment adjacent to said inner frame case bypasses the torque box.

10. A gas turbine engine comprising: a primary fluid flow path defined at least in part by a compressor section, a combustor section, and a turbine section; a mid-turbine frame disposed in said turbine section between a first turbine portion and a second turbine portion; said mid-turbine frame structurally supporting a bearing associated with said first turbine portion and providing cooling air to said second turbine portion; and wherein the mid-turbine frame includes an inner frame case defining a sealed torque box cavity, a plurality of spokes protruding radially outward form the inner frame case, and at least one service line connected to the inner frame case each of said spokes including a cooling passage extending from a radially outward end of the spoke toward the inner frame case, wherein the cooling passage is sealed at a joint between the inner frame case and the spoke.

11. The gas turbine engine of claim 10, wherein said at least one service line connects to a bearing support passage in said sealed torque box such that fluid is passed through said torque box through said bearing support passage to said bearing.

12. The gas turbine engine of claim 10, wherein each opening in said sealed torque box is sealed such that fluid exchange between said torque box and fluid external to said torque box is minimized.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 schematically illustrates a gas turbine engine according to one example.

(2) FIG. 2 schematically illustrates an isometric view of an exemplary mid-turbine frame for a gas turbine engine.

(3) FIG. 3 schematically illustrates a radial cross sectional view of the exemplary mid-turbine frame of FIG. 2 along a spoke.

(4) FIG. 4 schematically illustrates a radial cross sectional view of the exemplary mid-turbine frame of FIG. 2 along a service line.

DETAILED DESCRIPTION OF AN EMBODIMENT

(5) FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.

(6) The exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.

(7) The low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54. A combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54. A mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46. The mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28. The inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.

(8) The core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46. The mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C. The turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion. It will be appreciated that each of the positions of the fan section 22, compressor section 24, combustor section 26, turbine section 28, and fan drive gear system 48 may be varied. For example, gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.

(9) The engine 20 in one example is a high-bypass geared aircraft engine. In a further example, the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine 46 has a pressure ratio that is greater than about five. In one disclosed embodiment, the engine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1). Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle. The geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.

(10) A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (1066.8 meters). The flight condition of 0.8 Mach and 35,000 ft (1066.8 m), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)]{circumflex over ( )}0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 m/s).

(11) The exemplary gas turbine engine 20 described above includes a mid-turbine frame (MTF) 57 that has an inner frame case. The inner frame case surrounds and supports a high spool bearing. Defined within the inner frame case is a cavity referred to as a torque box. The mid-turbine frame 57 is positioned between the low pressure turbine section 46 and the high pressure turbine section 54. As a result of the position of the mid-turbine frame 57 in the flow path, the mid-turbine frame 57 is exposed to high temperatures.

(12) In order to pass oil through the primary flow path to the radially inward portions of the gas turbine engine 20, such as a high spool bearing supported by the mid-turbine frame 57, service lines pass through the torque box.

(13) In some designs, cooling air for the low pressure turbine is fed into the torque box, and directed from the torque box to the low pressure turbine. In the event that an oil leak from the bearing compartment, or the service lines occurs, oil can leak into the torque box. In systems directing cooling air through the torque box to the low pressure turbine, compounds, such as oil, within the torque box can be directed toward the low pressure turbine along the same flow path as the cooling air.

(14) FIG. 2 schematically illustrates an isometric view of an exemplary mid-turbine frame 57 for a gas turbine engine, such as the gas turbine engine 20 of FIG. 1. The mid-turbine frame 57 includes multiple spokes 110 extending radially outwardly from an inner frame case 120 and distributed circumferentially about the inner frame case 120. Each of the spokes 110 is hollow, and includes a cooling passage 112 allowing cooling air to be passed radially inward toward the torque box defined within the inner frame case 120. A radially outward end of each spoke 110 includes a flange 114, or other connection feature, for connecting the spoke 110 to an engine case and to a cooling air system. In addition to including a cooling passage 112 for providing cooling air to the low pressure turbine, each of the spokes 110 structurally supports the inner frame case 120. The inner frame case 120, in turn, structurally supports a high spool bearing (not pictured) disposed radially inward of the inner frame case 120. Alternatively, the mid-turbine frame 57 can support different bearing systems depending on the structural needs of a given turbine engine including the mid-turbine frame 57.

(15) Also protruding radially outward from the inner frame case 120 are multiple service lines 130. Each of the service lines 130 includes a connection feature 132 at a radially outward end of the service line 130. The connection feature 132 can be any known connection feature type and allows the service line 130 to be fluidly connected to an oil source radially outward of the primary flow path. In alternative systems, fluids distinct from oil can be passed through one or more of the service lines 130. At the radially outward surface of the inner frame case 120, each service line 130 passes through a corresponding service line seal 134 into the torque box. The service line 130 exits the torque box at a radially inward surface through a corresponding service line seal, and provides the oil to the high spool bearing, or any other system radially inward of the mid-turbine frame 57. The torque box 140 is sealed at each opening for the service line 130 pass through, and at the radially inner end of each spoke 110.

(16) Further, any additional openings in the torque box 140 are sealed using appropriate sealing features. The sealing of the torque box 140 in this manner minimizes fluid leakage into the torque box, and minimizes leakage of fluids out of the torque box.

(17) With continued reference to FIG. 2, and with like numerals indicating like elements, FIG. 3 schematically illustrates a cross sectional view of the exemplary mid-turbine frame 57 of FIG. 2 along cross section A-A. Illustrated in FIG. 3 is a single spoke 110 with the cooling passage 112 described above. A practical implementation will include multiple approximately identical spokes 110 distributed circumferentially about an axis defined by the mid-turbine frame 57. Disposed radially inward of the spoke 110, and defined by the inner frame case 120 is a torque box 140. A plug 116, or other seal element, blocks the radially inward end 115 of the cooling passage 112 through the spoke 110. The plug 116 completely seals the radially inward opening of the cooling passage 112. In alternative examples, the cooling passage 112 can extend only partially through the spoke 110 and there is no opening at the radially inward end 115. In such an example, the plug 116 is omitted.

(18) In order to provide coolant to the low pressure turbine section 102, a coolant redirection tube 113 protrudes aft from the spoke 110 and provides a coolant flow path from the cooling passage 112 into the low pressure turbine section 102. By redirecting coolant flowing through the spoke 110, the illustrated mid-turbine frame 57 avoids passing coolant through the torque box 140 entirely. The torque box 140 also includes multiple service line pass throughs and bearing support passages that are out of plane in the cross section of FIG. 3. The exemplary bearing support passages are illustrated in FIG. 4, and are described below. The joint between the spoke 110 and the torque box 140 is sealed using any known seal type, thereby preventing fluid transferring into and out of the torque box 140.

(19) With continued reference to FIGS. 2 and 3, and with like numerals indicating like elements, FIG. 4 schematically illustrates a radial cross sectional view of the exemplary mid-turbine frame 57 of FIG. 2 along cross section B-B. Cross section B-B is drawn radially along a service line 130, and illustrates the torque box 140, and bearing support passage 150 surrounded by the torque box 140.

(20) The service line 130 includes a connection feature 170 including flanges 172 and a seal element 174. The connection feature 170 of the service line 130 connects to the bearing support passage 150 within the torque box 140. The service line connection feature 170 is sealed to the bearing support passage 150 via a seal element 174. The seal element 174 in the illustrated example is a piston seal. In alternative examples, any sealing element capable of sealing the service line 130 to the bearing support passage 150 can be utilized in place of the piston seal. The seal element 174 is disposed between an outward facing surface of an extension portion 173 of the service line connection feature 170 and an inward facing surface of the bearing support passage 150. The extension portion 173 extends into the bearing support passage 150. By sealing the interface between the service line 130 and the bearing support passage 150 in this manner, oil leaks from the service line 130 into the torque box 140 are minimized.

(21) Disposed radially outward of the service line connection feature 170 is an inner frame case seal plate 176. The inner frame case seal plate 176 is sealed to the inner frame case via a piston seal 178. In alternative examples, alternative seal types capable of functioning in the mid-turbine frame environment could be utilized in place of the piston seal. The piston seal 178 prevents oil, and mid-turbine frame air, from outside of the inner frame case 120 from leaking into the torque box 140 through the interface between the connection feature 170 and the bearing support passage 150. The piston seal 178 also prevents any fluids within the torque box 140, from being passed out of the torque box 140 into the adjacent portions of the turbine engine.

(22) The bearing support passage 150 inside the torque box 140 provides oil to a bearing supported by the mid-turbine frame 57. The radially inward openings 152, 154 through which the bearing support passage 150 passes are similarly sealed at each opening 152, 154, preventing flow into and out of the torque box 140 at the radially inward portion of the bearing support passage 150.

(23) As a result of the sealing features described above with regards to FIGS. 3 and 4, the torque box 140 is a sealed torque box, and fluids are not communicated into or out of the torque box 140.

(24) With continued reference to FIGS. 1-4, the above described configuration provides a configuration that is capable of minimizing the possibility for mid-turbine frame air from entering into the torque box 140. The possibility is further reduced by sealing the torque box from adjacent engine sections, and prevent the exchange of fluids between the torque box and adjacent engine portions including the cooling air flow being directed to the low pressure turbine. One of skill in the art, having the benefit of this disclosure will understand that while an ideal seal prevents all fluid exchange between both sides of the seal, practical seals will have a minimal amount of fluid exchange. Reference herein to minimized transfer of fluids across a seal is in reference to this practical reality.

(25) It is further understood that any of the above described concepts can be used alone or in combination with any or all of the other above described concepts. Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.