US3830060A

US3830060A - Solid medium thermal engine

Info

Publication number: US3830060A
Application number: US00336319A
Authority: US
Inventors: J Jedlicka; Le Roy Guist; R Beam
Original assignee: National Aeronautics and Space Administration NASA
Current assignee: National Aeronautics and Space Administration NASA
Priority date: 1973-02-27
Filing date: 1973-02-27
Publication date: 1974-08-20
Anticipated expiration: 1991-08-20

Abstract

A thermal engine apparatus including an elongated cylindrical tube of metal providing a single phase working substance supported to rotate freely about its longitudinal axis while being subjected to continuous bending moment producing stress loads applied intermediate its ends wherein the bending moment causes portions of the tube to alternately pass through states of compression and tension as the tube rotates about its axis. The apparatus further includes structure for positioning the cylindrical tube relative to a source of radiant energy such that the radiant energy strikes that portion of the tube surface which is under compression, transfers thermal energy thereto, and the consequent expansion creates an unbalance of internal forces which causes the body to rotate about its axis.

Description

United States Patent Jedlicka et al.

[111 I 3,830,060 Aug. 20, 1974 SOLID MEDTUM THERMAL ENGINE [75] Inventors: vJames R. Jedlicka, Saratoga; Le Roy R. Guist, Campbell; Richard M. Beam, Santa Clara, all of Calif.

[73] Assignee: The United States of'America as represented by the Administrator of the National Aeronautics and Space Administration, Washington, DC.

[22] Filed: Feb. 27, 1973 [21] Appl. No.: 336,319

[52] US. Cl. 60/527 [51] Int. Cl. F03g 7/06 [58] Field of Search 60/23, 26

[56] References Cited UNITED STATES PATENTS 182,172 9/1876 Crookes 60/26 3,121,265 2/1964 Hoh 60/26 3,665,705 5/1972 Christensen 60/23 FOREIGN PATENTS OR APPLICATIONS 307,596 3/1929 Great Britain 60/26 Primary Examiner-Edgar W. Geoghegan Assistant Examiner-11. Burks, Sr.

Attorney, Agent, or FirmDarrell G. Brekke; Armand G. Morin, Sr.; John R. Manning [57] ABSTRACT A thermal engine apparatus including an elongated cylindrical tube of metal providing a single phase working substance supported to rotate freely about its longitudinal axis while being subjected to continuousbending moment producing stress loads applied intermediate its ends wherein the bending moment causes portions of the tube to alternately pass through states of compression and tension as the tube rotates about .its axis. The apparatus further includes structure for positioning the cylindrical tube relative to a source of radiant energy such that the radiant energy strikes that portion of the tube surface which is under compression, transfers thermal energy thereto, and the consequent expansion creates an unbalance of internal forces which causes the body to rotate about its axis.

12 Claims, 8 Drawing Figures PATENTEUmczo 1914 3. 830.06 0

sum 20? 3 Q=5.6 kw/ m (4 SOLAR CONSTANTS) 0 83 MN/ m uzooo #/in [,4 TOTAL MEASURED POWER T oT L |3owER THEORY,eq.(40) E UNSTABLE 3 FRICTION AND AERODYN. S 15- '1 POWER LOSSES O E 0: LL! 8 8 .6-

.lo NET POWER OUT NET TORQUE l J O o .5 L0 |.5 2 o SPEED,S, rps H PATENTEMuszo I914 mm 30; 3 3.830.060

sum RAYS POSITION SU N CONTROL LOCATOR no I LINERTIALLY STABILIZED PLATFORM POSITION SUN CONTROL POSITION D ETECTO R SOLID MEDIUM THERMAL ENGINE BACKGROUND OF THE INVENTION The invention generally relates to thermal engine apparatus and more particularly to thermal engines using a single phase metallic working substance to convert thermal energy directly into mechanical energy.

DESCRIPTION OF THE PRIOR ART Thermal engines operating pursuant to the principles of thermal expansion of metals have been proposed in the past. For example, structures such as that shown in the U.S. Pat. to Taylor No. 3,316,415 rely on the use of bi-metallic strips moving on rollers to convert heat induced metallic expansion into a resultant body motion. Other structures such as that disclosed in the U.S. Pat. to Donatelli, et al., No. 3,495,406 rely on laser beam energy or the like to exert direct physical force upon a rotary member to cause the member to rotate. A still further structure described in the U.S. Pat. to Adams, No. 3,430,441, provides an engine for converting heat energy to mechanical energy by thermal expansion and contraction of bi-metallic elements which are passed through heating and cooling zones established within an engine housing.

The direct conversion of heat energy into mechanical energy through the thermal expansion properties of solids has been utilized for control and measurement functions as illustrated by the U.S. Pat. Nos. to Lord, 3,213,284, and McCusker, 3,213,285 relating to heliotropic orientation mechanisms. The U.S. Pat. to Schalkowsky, No. 3,348,374, refers to a sun referenced orientation device in which solar energy is directly converted to mechanical forces for orientating space vehicles relative to the position of the sun. Although these and numerous other approaches have been proposed and utilized to provide thermally driven motive power sources, most prior art devices have been so mechanically complicated or grossly inefficient as to be impracticable.

SUMMARY OF THE PRESENT INVENTION It is therefore a principal object of the present invention to provide a thermal engine which is mechanically simple and operationally feasible for certain applications.

Briefly, a preferred embodiment of the present invention includes a single phase working substance in the form of a generally cylindrical metallic tube supported such that it is free to rotate about its axis while being subjected to continuous bending moment stressing the body along its longitudinal axis of rotation. The stressing causes certain portions of the tube to be subjected to compression while other portions are under tension as the tube is caused to rotate about its axis. Means are provided for positioning the tube such that radiant energy from a remote source is concentrated on that portion of the cylindrical tube which is under maximum compression with the result being that heat absorbed by this portion causes an imbalance of internal forces which tend to impart a rotational moment to the tube so that it rotates about its axis.

Among the primary advantages of the present invention are its simplicity of operative mechanical structure and its ability to function in a gravity free environment.

These and other objects and advantages will no doubt become apparent to those of ordinary skill in the art after having read the following detailed description of the preferred embodiments illustrated in the several figures in the drawings.

IN THE DRAWINGS FIG. I is a perspective view schematically illustrating a thermal engine apparatus in accordance with the present invention;

FIGS. 2-5 are schematic diagrams to aid in describing the operation of the present invention;

FIG. 6 is a diagram illustrating measured operational characteristics of one embodiment of the present invention;

FIG. 7 is a perspective diagram schematically illustrating an alternative embodiment of the present invention for use in a gravity-free environment;

FIG. 8 is a diagram schematically illustrating still another alternative embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to the drawings, a simplified embodiment of a thermal engine 10 is shown in FIG. l which operates to convert thermal energy directly into rotational kinetic or mechanical energy in accordance with the present invention. Engine 10 includes a thin walled cylindrical tube 12 formed of a suitable metal to provide a single phase solid working body. The exterior surface of tube 12 is coated with a thin layer of flat black paint or the like to increase the absorptivity and emissivity of the body. Cylindrical extension shafts l4 and 16 are fixed to opposite ends of tube 12 and mate with a pair of

support columns

18 and 20.

Shafts

14 and 16 are disposed coaxial with tube 12 and are journaled to

columns

18 and 20 by means of

support bearings

22 and 24 respectively.

External loading masses in the form of

annular weights

26 and 28 are coaxially mounted upon the shafts l4 and 16 respectively, at selectable distances from the

columns

18 and 20. The

weights

26 and 28 establish uniform longitudinal bending moments which continuously stress tube 12 so that its uppermost longitudinal portion is subjected to compression and its lower most longitudinal portion is subjected to tension.

Bearings

22 and 24 permit the balanced mass comprised of tube 12, shafts I4 and 16 and

weights

26 and 28 to rotate freely about the common axis 13. Since the stressing forces applied by

weights

26 and 28 are fixed in direction due to gravitational forces, the bending stresses withintube 12 remain positionally fixed independent of the bodies rotation. Thus, with tube 12 stationary or in rotation, the topside longitudinal portion (illustrated as the upper quarter sections I and II in FIG. 4) is always under compression relative to the bottomside longitudinal portion (illustrated as the lower quarter sections III and IV in FIG. 4) and the bottomside portion is always under tension relative to the topside portion.

As suggested by the drawing, tube 12 is positioned in alignment with a source of heat radiation illustrated in the form of a bank of lamps 30 disposed such that the heat rays generated thereby are focused upon at least part of that portion of tube 12 which is under compression. The thermal flux intensity may be controlled by changing the distance between the bank of lamps 30 and tube 12. The lamps are positioned slightly off the vertical plane (by about 5) so that the engine will be self-starting. No heat is applied to the bottomside of tube 12 and preferably, conditions are such that heat is readily removed therefrom by radiation or convection.

As the temperature of the upper portion of tube 12 is increased due to the incident radiation, the metal in that portion will tend to expand and disrupt the balanced equilibrium conditions with the result being that a torque is developed within tube 12 which causes the tube to revolve about its axis 13.

Referring now 'to' FIGS. 2-6 a more detailed analysis will be given to explain the operating mechanisms of the present invention.

If an element 40 of a solid such as illustrated in FIG. 2 is first loaded externally to produce a stress distribution on its opposite surfaces and then heated to produce a temperature increase AY,.the work Aw done on the external loading due to the temperature increase is AW=0,,A aATAx P AW/At o' Ax (AT/At) Ax The rate of change of temperature with respect to time t is related to the thermal power P, into the element so that a P, pcA Ax (AT/At) (3) where p and c are the density and specific heat of the solid. If the thermal efficiency of the process is denoted by e then from equations (2) and (3) e P /P, o alpc (unidirectional stress) If the applied stresses (T1 are reversed in direction during the cooling portion of a cycle, the thermal efficiency for the complete heating and cooling cycle is e1 Po/P, 2a,a/pc (bidirectional stress) ll the element is placed under triaxial stress instead of uniaxial stress, the thermal efficiency is increased threefold to e 6a,,a/pc (tn'axial, bidirectional stress) For a system utilizing the solid phase cycle and nonregenerative heating, equations (4), (5), and (6) represent the maximum thermal efficiencies that can be attained.

As described above a simple design of a solid phase engine which utilizes uniaxially stressed material consists of a tube, such as that shown in at 12 in FIG. 1 and schematically illustrated at in FIG. 3, that is free to rotate but has an applied moment fixed in the inertial reference frame. The inertial coordinate system is defined as xyz. The tube 50 is free to rotate about the xaxis and no moment can be carried by the end supports 52 and 54 (pinned ends). The applied moment vector, M (x) identified in FIG. 4, is assumed to remain parallel to the z axis. The moment may be due to the weight of the cylinder or applied loading. The thermal loading is provided by a planar flux field of radiant energy with magnitude 0,, which acts normal to the x-axis and at an angle 1' with the y-axis'(FIGS. 3 and 5 If 0 is the circumferential coordinate measured from a reference point fixed to the tube 50 (FIG. 5) and R and h are the radius and wall thickness of the tube 50,

the differential power produced by an element of the tube is from equation (2),

and the total power produced by the engine is obtained by integrating expression (7) over the whole tube 50:

If the tube is rotating at constant angular velocity (0, the stress is related to the moment from simple beam theory where for R h:

To complete the computation of the power output from equation (8), it is necessary to evaluate the temperature distribution in the tube 50. The heat balance equation for a ring element of the tube of unit length in the x direction is 5 6 the circumference will be small compared to the aver- T -{R Q a,, cos[n1] arctan p /(q age temperature (T of the tube, that is, n2)]}/khpn[ (q 2 p 2 1/2 where p is the negative reciprocal of the Fourier modulus If condition (1 l) is introduced into the heat balance (URI/k equation and only first-order terms retained, one p PC obtains kha fl (in/R 80 pch8T( (an/s1 4TA3T(0J) and If the thermal absorptivity of the tubes surface is a and the tube is rotating with constant angular velocity Wlth the notatlo w, the function 'y(6,t) becomes A" Rza1Qlflh/khpnu (q n2)/( 2 112 7( rQog( l 20 22 1 arctan pn/(q n (17/2) 1 s (qr/2) where g is a functional relationshlp. Expressed as a Fourier series representation, 25 (23) the solution to the heat balance equation (12) with as thermal input y defined by equation (14) can be writ- 'Y( rQoE n 008 ten The steady state or particular solution for equation T t T I 0 (12) with y defined by equation (14) can be written A 2 005 [n(0+w ll) (m (24) T0,t= T 0,t) and l where 7,, (0,!) is the solution to the equation T: Sin l l')nl The output power of the engine [equation (8) may For all n 0; now be computed with expressions (9) and (25) as 4 1r gen T P =[Ci/1rR]J M ($)dIf cos (tH-wt) since T has been assumed time independent. A partic- 0 ular solution to equation 16) can be easily obtained in 2 MA sin [n(0+w, ll,) n|d9 the form (26) nui u an n (17) However, this can be reduced to 6 Introduction of A from equation (22) into the power 0 equation produces where a prime is used to denot differentiation with re- If the radiant heat absorbed by an element is assumed spet to 1;. to be proportional to the cosine of the angle between A particular solution to equation (18) is the normal to the surface and the thermal radiation direction (Lamberts law), then the function g, required in equation (13), becomes g( Hail-111) and a,, required in equation (28), becomes 2 a =[f cos n cos 1 dn]/f cos n d1;=1/2

The power output equation becomes therefore, the thermal efficiency can be written or with thermal radiation on top of the tube (1' 0):'

T max p In an experimental engine built along the lines illustrated in FIG. 1 the working substance was stainless steel (type 304 annealed) which has been welded into 5 a thin walled cylindrical configuration to form tube 12.

The surface of tube 12 was sprayed with a thin coat of are valid. If these conditions are introduced into the. power equation (31 and the phase angle equation (23) one obtains Thus the power is maximum if the thermal radiation is on top" (l 0) of the tube and zero if the thermal radiation is to the side (I i1r/2) of the tube. Note also that the power output is negative if I Il 17/2 (but less than 77').

If the applied moment distribution is uniform along the length of the tube (M, (x) M,,,,) then P (M aa Q l/2hpcR)siri[tl1 (1r/2)] The thermal power input to the engine is P,- 2a Q Rl therefore, the thermal efficiency is e (M a/4hpcR )sin[I,l1 +(1'r/2)l I The maximum stress in the tube is related to the mo ment by flat black paint to increase absorptivity and emissivity. An almost uniform bending moment was applied to tube 12 by

annular weights

26 and 28 mounted on

shafts

14 and 16 between the ends of tube 12 and the

support bearings

22 and 24. The stress applied to tube 12 was easily varied by translating the weights along the shafts.

Radiant energy was provided in the laboratory by a string of photographers photo-spot lamps, and the thermal flux intensity on the tube 12 was controlled over a range of one to a maximum of about five solar constants by changing the distance between the lamps and the tube. The lamps were positioned slightly off the vertical plane by about 5 so that the engine would be self starting. The performance data for the experimental engine is shown graphically in FIG. 6.

Net torque was measured by a Prony break, and the net power output was computed. Frictional aerodynamic and visco-elastic power losses were established from the lamps-off (at operating temperature) decay rates of the engine speed. The total power output curve is the sum of the power loss in the new power.

The thermal energy passing through the working substance was determined with the aid of a transient calorimeter constructed with the curvature of the tube 12 and sprayed with a thin coat of flat black paint. The theoretical power output shown in FIG. 6 was obtained by multiplying the theoretical thermal efficiency factor (equation 40) by the experimentally determined thermal energy input. The discrepancy between theory and experiment could be attributed to many factors, however, the most probable sources of error were (a) accuracy of material properties used in calculating theoretical efficiency, (b) accuracy of the loss measurements since these data were taken for lamps-off condition (although near operating temperature), and (c) accuracy of the experimental determination of the thermal input to the tube.

heat transfer at the conditions of the test, the two will be comparable in magnitude. Additional analysis not included here demonstrates that the thermal efficiency is governed by the circumferential variation in the heat transfer rather than by its magnitude. If all heat were rejected at the tube bottom rather than uniformly around the tube for example, the thermal efficiency would increase by a factor of 2. Forced convection caused by the angular velocity of the tube should give rise to heat rejection uniform with respect to circumference and therefor will predict the same thermal efficiency as for radiation. If natural convection dominates however, heat rejection will be largest at the bottom of the tube and the thermal efficiency would be increased.

Two types of instabilities were encountered in the operation of the experimental engine, one at low speeds and one athigh speeds. Both instabilities were apparently due to the coupling of the thermal input and the tube deformations. The low speed instability range is indicated in FIG. 6. At these speeds a thermally induced bow forms in the tube which produces an unbalance of the rotating weights. Because of the unbalance the bowed region moves at lower angular velocities when passing the heat input plane thereby causing an increase in the amount of thermal bow.

The amplitude of the bow increases until the unbalance is so large that the engine rotation ceases. However, rotation can be restored by reducing the torque loading to a value that permits the engine running speed to exceed the minimum instability speed.

The second instability occurred when the engine was operated at speeds near one-half the first critical speed, defined as the speed corresponding to the first mode bending frequency of the tube. When this speed was approached, a thermally coupled operational instability occurred which rapidly built up without apparent limit cycle.

The relatively high losses of the experimental engine reflected in FIG. 6 have been determined to result from joint slippage in the connection between the shafts and the tube and in a later modification in which the joint was welded the losses were significantly reduced.

' Referring now to FIG. 7 of the drawing, an embodiment similar to that of the FIG. 1 embodiment, but modified for use in a gravity-free environment such as outer space, is shown at 110. As in the previous embodiment the structure includes a cylindrical tube 112 forming a working

body havingshafts

114 and 116 affixed to each end. The shafts are journaled to a pair of

supports

118 and 120 by

bearings

122 and 124. The primary difference between this embodiment and that previously described is that since there are no gravity forces to act upon annular stressing weights, means must be provided for simulating the gravity function. In this case, such stressing forces are applied by means of spring loaded bearing

structures

126 and 128 which apply biasing forces downwardly toward the support base 119. A suitable radiation focusing means 130 is positioned to focus rays of sunlight or other radiation onto a particular longitudinal portion of tube 112.

Since the apparatus 110 must always be oriented so that the focusing means 130 can focus sun rays onto a particular portion of tube 112, means such as the inertially stabilized platform schematically illustrated at 160 must be provided along with a suitable sun position locating means 162 and an engine position control mechanism 164. Locator 162 detects the relative position of the sun and develops an output signal for energizing position control means 164 causing it .to maintain engine oriented in the proper direction relative to the sun.

Still another alternative embodiment of the present invention can be constructed without weights for use in a non-gravitational environment by closing the tube upon itself to form a torus 212 as illustrated in FIG. 8 of the drawing. The tube must undergoonlyv elastic bending when it is formed into a torus. Torus212 is likewise coated with a layer of black paint or the like to increase its absorptivity and emissivity, and is suspended within a housing 214 by any suitable means. For example, ring magnets 216 may be positioned within housing 214 for creating a magnetic field to magnetically suspend the torus within housing2l4. Positioned at the bottom of housing 214 and aligned with the central aperture of torus 212 is a parabolic reflector 218 which is designed to reflect radiation from the sun onto a particular portion of the facing surfaces of the torus.

Housing 214 is provided with a circular opening 220 for allowing the sun rays to reach reflector 218 while at the same time masking rays which would otherwise impinge directly upon the surface of torus 212. Where this embodiment is to be used in an outer space embodiment a suitable guidance reference such as the suggested inertially stabilized platform 260 may be providedfor carrying a sun locator 262 and a position control means 264 as in the previous embodiment. Sun detector 262 will detect the relative location of the sun and generate an electrical signal for energizing control means 264 which will in turn orient engine 210 in the proper direction to receive the rays of sunlight.

In operation, as the solar rays are received and reflected by reflector 218 onto a particular quarter section of torus 212, the metallic fibers in the irradiated region will tend to expand due to the increase in temperature and as in the previous embodiment create internal forces within torus 212 which tend to impart rotary motion to the structure causing it to roll about its own axis. In order to provide a power take-off, any suitable means of coupling may be provided which is com sistent with the particular suspension mechanism utilized. It will be appreciated that in this embodiment heat applied to the inner annular surfaces of the torus will enable the device to deliver power without the use of either weights or externally loaded bearings to stress the cylindrical body.

Whereas the above description has been limited to three simplified embodiments it is to be understood that these embodiments are greatly simplified and offered for purposes of illustration only. It is contemplated that after having read the above disclosure, one of ordinary skill in the art will envision many other alterations, modifications and further embodiments of the invention. It is therefore to be understood that the above disclosure is not to be taken as limiting and that the appended claims are to be interpreted as covering all such alterations and modifications as fall within the true spirit and scope of the invention.

We claim:

1. Thermal engine apparatus, comprising:

a generally tubular body having a circular transversev cross section mounted for rotation about its axis of symmetry, said body having axially directedcompressive forces developed therein on one side of saidaxis and axially directed tensile forces developed therein on the opposite side of said axis; and

means for heating the compression loaded side of said body whereby the resultant expansion causes internal forces to be developed within said body tending to impart rotational motion of said body about said axis.

2. Thermal engine apparatus as recited in claim 1 wherein said body includes an elongated tubular member journaled at one end to means for applying a clockwise bending moment to said body and journaled at the opposite end to means for applying a counterclockwise bending moment to said body, said bending moments being operative to develop additional compressive and tensile forces in said body.

3. Thermal engine apparatus as recited in claim 1 wherein said body includes an elongated tubular member bowed end-to-end to form a torus having said compressive forces developed within its inner annular portion and said tensile forces developed within its outer annular portion.

4. Thermal engine apparatus for converting radiant energy to rotational kinetic energy comprising:

a hollow, elongated, generally cylindrical body dis- 7 posed to have its longitudinal axis lying along the intersection of an imaginary horizontal plane and an imaginary vertical plane, said body being divided by said planes into four imaginary longitudinal quadrants;

stressing means for applying forces to said body for causing the quadrants disposed on one side of said planes to be subjected to compression and the quadrants disposed on the opposite side of said one plane to be subjected to tension; and

means for positioning said body relative to a source of radiant energy so that said radiant energy strikes one of said quadrants subjected to compression and transfers thermal energy thereto, said positioning means including means for rotably supporting said body about said axis, said thermal energy causing expansion, increased stress, and rotary motion in said body, said rotary motion being about said longitudinal axis.

5. Thermal engine apparatus as recited in claim 4 wherein said stressing means includes means for applying a clockwise moment lying in said vertical plane to one end of said body and for applying a counterclockwise moment lying in said vertical plane to the other end of said body.

-6. Thermal engine apparatus as recited in claim 4 wherein said body includes a metallic tubular member having an exterior surface coated with a layer of optically black material having better heat absorptivity and emissivity characteristics than said member.

7. Thermal engine apparatus as recited in claim 4 and further comprising means for directing radiant energy onto said body, and wherein said means for positioning said body includes a sun locator and servo means for orienting said body so that the radiant energy from the sun impinges on one of said body quadrants subjected to compression.

8. Thermal engine apparatus as recited in claim 4 wherein said stressing means includes a collar-like weight member disposed about said body.

9. Thermal engine apparatus as recited in claim 4 wherein said means for positioning said body includes a first end support and a second end support respectively engaging opposite-ends of said body, and wherein said stressing means includes force applying means located adjacent each of said end supports and operative to apply forces which tend to bend said body in an arc.

10. Thermal engine apparatus as recited in claim 9 wherein said force applying means includes a first collar-like weight member disposed about said body proximate one end of said body, and a second collar-like weight member disposed about said body proximate the opposite end of said body.

11. Thermal engine apparatus as recited in claim 9 wherein said force applying means includes means journaled to said body and affixed to said end support means for applying transverse loading to said body.

- 12. Thermal engine apparatus, comprising:

an elongated tubular member closed upon itself to form an annular body having an inner annular portion subjected to compressive stress and an outer annular portion subjected to tensile stress; and

means for applying heat to said inner annular portion whereby resultant expansion of that portion creates forces within said body which tend to cause the portion of said body presently forming said inner annular portion to rotate into the position of the portion of said body forming said outer annular portion and vice versa.

Claims

1. Thermal engine apparatus, comprising: a generally tubular body having a circular transverse cross section mounted for rotation about its axis of symmetry, said body having axially directed compressive forces developed therein on one side of said axis and axially directed tensile forces developed therein on the opposite side of said axis; and means for heating the compression loaded side of said body whereby the resultant expansion causes internal forces to be developed within said body tending to impart rotational motion of said body about said axis.

2. Thermal engine apparatus as recited in claim 1 wherein said body includes an elongated tubular member journaled at one end to means for applying a clockwise bending moment to said body and journaled at the opposite end to means for applying a counter-clockwise bending moment to said body, said bending moments being operative to develop additional compressive and tensile forces in said body.

4. Thermal engine apparatus for converting radiant energy to rotational kinetic energy comprising: a hollow, elongated, generally cylindrical body disposed to have its longitudinal axis lying along the intersection of an imaginary horizontal plane and an imaginary vertical plane, said body being divided by said planes into four imaginary longitudinal quadrants; stressing means for applying forces to said body for causing the quadrants disposed on one side of said planes to be subjected to compression and the quadrants disposed on the opposite side of said one plane to be subjected to tension; and means for positioning said body relative to a source of radiant energy so that said radiant energy strikes one of said quadrants subjected to compression and transfers thermal energy thereto, said positioning means including means for rotably supporting said body about said axis, said thermal energy causing expansion, increased stress, and rotary motion in said body, said rotary motion being about said longitudinal axis.

5. Thermal engine apparatus as recited in claim 4 wherein said stressing means includes means for applying a clockwise moment lying in said vertical plane to one end of said body and for applying a counter-clockwise moment lying in said vertical plane to the other end of said body.

6. Thermal engine apparatus as recited in claim 4 wherein said body includes a metallic tubular member having an exteRior surface coated with a layer of optically black material having better heat absorptivity and emissivity characteristics than said member.

9. Thermal engine apparatus as recited in claim 4 wherein said means for positioning said body includes a first end support and a second end support respectively engaging opposite ends of said body, and wherein said stressing means includes force applying means located adjacent each of said end supports and operative to apply forces which tend to bend said body in an arc.

12. Thermal engine apparatus, comprising: an elongated tubular member closed upon itself to form an annular body having an inner annular portion subjected to compressive stress and an outer annular portion subjected to tensile stress; and means for applying heat to said inner annular portion whereby resultant expansion of that portion creates forces within said body which tend to cause the portion of said body presently forming said inner annular portion to rotate into the position of the portion of said body forming said outer annular portion and vice versa.